Wichita State University Libraries
SOAR: Shocker Open Access Repository
Wind Energy Reports, no.37 rev
Center for Energy Studies
Performance and Aerodynamic Braking of a Horizontal-Axis Wind
Turbine from Small-Scale Wind Tunnel Tests
Hoa Cao and W.H. Wentz Jr.
Wichita State University
Recommended citation
Hoa Cao and Wentz, W.H. Performance and Aerodynamic Braking of a Horizontal-Axis Wind Turbine
from Small-Scale Wind Tunnel Tests. Wichita, Kan: Wichita State University, 1985. -- 116 p.
Digitized by University Libraries and posted in Shocker Open Access Repository
Citable Link: http://soar.wichita.edu/dspace/handle/10057/5661
Terms of use: in the Public Domain
WER-37rev
WIND ENERGY REPORT NO. 37
PERFORMANCE AND AERODYNAMIC
BRAKING OF A HORIZONTAL-AXIS
WIND TURBINE FROM SMALL-SCALE
WIND TUNNEL TESTS '
by
H.V . Cao, and W.H. Wentz , Jr.
Center for Energy Studies
Wichita State University
Prepare d for NASA-Lewis Research Center
Grant No. NSG-3277
NASA Technical Monitor:
J.M. Savino
FOR EARLY DOMESTIC DISSEMINATION
Date o f General Release :
July, 1985
,
July, 198 7
WER -37 r ev
Wind Energy Report No . 37
PERFORMANCE AND AERODYNAMIC BRAKING
OF A HORIZ ONTAL-AXIS WIND TURBINE
FROM SMALL-SCALE
WIND TUNNEL TESTS
by
H.V . Cao, and W.H. Wentz , Jr.
Center for Energy Studies,
Wichita State University
Wichita, Kansas
This work has bee n funded by Lewis Research Center
of the National Aeronautics and Space Administration
by Research Grant No. 3277
NASA Technical Monitor:
J.M. Savino
FOR EARLY DOMESTIC DISSEMINATION
Because of its early ccmnercial pot ential, this infonnation, which has
been developed W1der a grant fran N!\SA., is being dissaninated within
the United States in advance of general p.1blication. 'Ihls infonnation
may be duplicated and used by the recipient wi th the
express
limitation that it not be p.Jblished. Release of this infonnation to
other danestic puties by the recipient shall be made subject to these
limi tations .
Fore ign release may be nade only with prior Nr\SA.
approval and appropriate exfOrt licenses . 'Ibi s statenent shall be
marked on any reproduction of thi s information in whole or in part .
DAT E FOR GENERAL RELEASE:
July, 1985
July, 1987
ABSTRACT
Wind tunne l
tests of three 20 -in ch diameter ,
zero-twist , zero - pitch wind turbin e rotor models have bee n
conducted in the WSU 7' x la ' wind tunnel
to determ in e the
p e rformance of such rotors wit h NACA 23024 airfo il a nd with
NACA 64)-621 airfoil sections .
Ae r odynamic braking
characteristics of a 30% span , 30% c hord vented ail eron
conf igura ti o n we r e measur ed on the NACA 23024 rotor .
Surface f l o w patterns were observed using f luo resce nt
mini - tufts attached to the suction side of the rotor
blades.
Experimental res ult s with and wi thout aileron are
compared to predic t ions using airfoil s ect i on data and a
momentum performa nce code.
Res ul ts of the performance
studies show that the 64 -621 rotor produces higher peak
3
power than the 2302 4 rot or for a given rotor RPM.
Analytical studies , however, indicate that the 23 024 should
produce hig her powe r.
Tra n s iti o n s trip experime nts show
that th e 23024 roto r i s much mo r e se nsiti ve to roughness
than the 64 -621 rotor.
3
predi ctions.
These trends agr ee with analytical
Results of the a il e ron t ests show tha t t hi s
ai l e r on , when deflec t ed , p r oduces negative torque at all
positive tip- speed ratios.
In free -wheeling coastdown s the
r otor blade stopped, then rotated backward a t a tip- speed
ratio of -0.6.
Results of the tuft studi es indicate that
substantial spa nwi se f l ow develops as blade stall occu rs at
low tip- speed rat i os .
1
LIST OF SYMBOLS
Ar e a swept by rotor disk , ' R2
C
Blade cho rd, feet
Cd
Coeffic i e nt of drag, drag/(O . S
pv/S)
c
Coeff icient of lift, lift/( O.S
pv/ S)
1
cn
Coefficient of normal fo rce , c1cos(Q) + c dsin(a)
Cs
Coefficie nt of suction , c 1s in(Q) - cdcos( a )
Cp
Coeffic i e nt of power , P/(qAdV)
Co
Co eff ici e nt of torque , Q/ (qAdR)
Coeffic i ent of thrust , T/ (qA )
d
Gravitational accele r ation , 32.2 ft/sec 2
M~
Freestream Mach number
M
Tip Mach number
P
Powe r, watts
q
Tunnel dynamic pressure , pst
Q
Torque , foot - pounds
r
Location along bl ade radius , percent R
R
Blade radius , inches
Re~
Frees tream Rey nolds number per unit l ength ,
Re t
Tip chord Reynolds number, Re~ (e)(l + TSR2)1/2
RPM
Rotat iona l veloci ty in r e volutions / minute
T
Thrust, pounds
TS
Transition Strips , each 0.005" thick x 0 . 10" wide
TSR
Tip- speed ratio , VT/ Vw
Vr
Local rotational ve locity , wr , ft/s e c
V
R
Res ultant ve l ocity, ft /sec
t
2
pVwc/u
V
T
Bl a de ti p ve l oci ty , wR, ft / sec
Vw
F r eest r eam o r wind ve locity , ft / sec or meter / sec
a
Ang l e of a ttack , degr e es
6
p
Angl e of aileron deflectio n ( negative upward)
2
Coe ffi c ient of dynamic v i scosity, Ib f - sec/ft
Air density, s lugs / ft 3
w
Angular ve l oc ity, r a di a ns / s e c
a
~
3
INTRODUCTION
One of the most crit i ca l design r equireme nts for large
scal e hor iz ontal- axis wind turbines is to provide costeffective , re l iable methods for overspeed cont rol.
Overspeed
protection is def initely needed wh en the r e is a sudde n loss of
e l ec trical load or i n very hig h wind conditi ons.
At the present time , large scale horizontal-axis wind
turbines uti liz e part ial or full spa n variabl e blade pitc h to
regulate rotor s peed.
In o rd e r
to pitch e it her t he f ull
l e ngth or a portion of a la rge wind turbin e blade , large blade
. pitch bearing as semblies and link ages are needed.
The design
of these systems poses several difficult str uctural and
mec hanical problems and adds cons ide rably to system we i ght and
cost (refe renc e 1).
Alternate methods which require much smalle r b e arings a nd
pi tch actuator systems , and therefo re appea r to have po t e ntial
fo r reducing rotor costs, a re th e use of spo i lers or ai l erons
as aerodynamic co ntr o l dev i ces .
Spoilers or ailerons, when
d e flected, change the lift and drag cha r ac t eris tic s of the
basic airfoi l, producing co rresponding c h a ng es i n ro t or
t o r que.
Pr i o r to t h e prese nt project , spoi l e rs of different sizes
a nd defle ct ion angles we r e t ested on an NACA 23024 a i rfoi l 2-D
model (reference 2) .
Due to prom i s ing resu l ts , these spoilers
we re later tes ted on a twenty-inc h diameter rotor
r
(r efe r e n ce 3) .
The results of these t ests show that the 20
4
percent chord spoiler at 90 d egree s angle of def l ection a nd
with hingeline position located a t 1 0 percent c hordlin e on the
upper surface of the airfo i l produced negative t o rque fo r all
tip- speed ratios greater than or equa l to 0 . 78 .
Howeve r,
si nce the blade structure is typically l ocated p rimaril y in
the forward 50 percent of the ai r fo il sec tion, it i s d iff icul t
to design a spoiler system for t hi s hing e li ne pos i t ion with out
a s i gnifica n t redu c tio n i n s tr e ng th , or alt e rnati ve ly , a
substantial increase i n weight .
Ailerons have also been evalua t e d a s a e r o d y nam ic co nt r ol
devices.
The primary reason for the pre f e renc e of ail e rons
ove r spoilers is that the entire moveabl e s urfac e i s located
on t he aft 50 pe r cent of the airfo il mak i ng it possible to
carry the main rotor structure (main s par) unint e rrupt e d f rom
hub to tip.
This simplifies and lig hte n s t h e s tr uc tur e .
Furthermore , ailerons , unlike spoi l e rs, ha v e the ca pabil i ty of
providing both positive and negat i ve incr eme nt s in lift. The
lift coeffic i ent can be increased by d ef l e c t ing th e a i le r o n
downward.
This increase in lift will ordinari ly r es ult in a n
increase in to rque .
This torque increme nt c a n be us e d to
increase the power output dur i ng ope rati on in l ow wind spee d
conditions.
For the purpose of ove r speed c ontro l, t he
rotational speed of the wind turb i ne can be r e duce d by
deflecting the aileron upward.
Upward a il e ron de f lecti o n will
ca use the lift to decrease which , in turn, reduces to r q u e .
Studies of predicted rotor perfo r ma n ce ba s e d o n wind tun ne l
tests of a il e rons on a 3- D reflection pl ane mode l
5
(refe r e nce 4 ) i ndi ca t e a st r o ng poss ibility o f s lowing the
rotor dow n t o a ver y low tip- speed ratio.
Th e purp o s e of the
pr ese nt p ro j e ct i s to e valu ate the per f ormance of the vented
def l ector- ail e r on in a t es t whi c h incl udes 3- D i nduc e d effects
and poss ible spa nwi se bound a ry laye r e ff e ct s .
Earl ie r s tudi es (ref e r e n ce 4) have sh own th a t a plain
( unv e nt e d ) aileron with or without lower sur f ace deflector was
adequate for power modulation , but inadequate for full
ae r o dynamic braking.
Thes e studi e s also revealed
discrepancies betwee n ana l ysis o f rotor performa nc e from 2-D
wind tunnel data and actual r o t o r p e rformance.
\ ' conclusions f rom the ear l i e r r esearch are:
The
(1) aileron
con t rol i s struc t urally and mecha nically f e asible;
r
(2) th e
ailerons t e s ted we re adequate f o r power modulation but
ma rginal f o r a erodynamic braking; (3) rotor a n a lysis codes are
ques tionabl e for pre dicting e ff e ctiveness of aerodynamic
b r a king devi ces , at least for on e case .
Thus , even though
ai rfo i l section tests and analysis indicate that the vented
ai l er on d e fl e ctor is adequat e , rotating tests are esse n tial
fo r v e rification.
Small scale wind tunnel te s ts have Reynolds
num ber and model d e tai l limitations , yet they are re lat ively
low- c o st, quick , and provide da ta of high quality in a
co ntrolled e nvironment .
It is on this basis that the present
t e s ts we re planned.
For this project a twe nty-inch diameter untapered ,
untwist e d , and unpitched rotor equipped with a n aileron over
the outboard 30% span was t ested.
6
The hing e line position was
designed such that an upwar d aileron deflection opens a gap
between the a il ero n and the airfo il as shown in figure 5.
Aileron chord was 30% , a nd a lower 20% chord solid e xte n s ion
plate was used to extend the lower surface of the aileron .
This configuration was deve loped in airfoil wind tunnel t ests
conducted ea rli er (ref e rence 4).
The purpose of the special
hin geline posit i on a nd the extension plate is to force a ir to
flow upwa r d t hr oug h the gap a t high angles of attack.
This
upwar d flow caus es th e lift to decrease , thus reducing
chordwise suction force .
Pe rformance characteristics of a clean (no aileron) NACA
2302 4 rotor and a clean NACA 64 -621 rotor were also studied
3
both experimen t a lly and analyt ically. Analytical results we r e
obtained by us ing t h e wind turbine performance computer
program WIND- II ( r e ference 5).
One purpose of the prese nt
s tudi es is to correl a t e roto r perfo rmance prediction f r om 2- D
data wi th r ota ting expe riments.
Surface flow patterns were studied using fluorescent
mini-tufts attached to the suction side of the rotor.
The
pu rp ose of the f low study was to determine the extent and
na tu r e of spanwise flow along the rotor at high angles of
attack .
Thi s r eport i s an extension of a master of science thesis
by the first autho r
(refere nc e 6).
This report includes
transition st rip results and addit ional analytical
ca l culations f r om WIND-II no t r e ported earlier.
7
BACKGROUND
The performance of a hor izontal axis wind turbine can
be a nalyz ed f r om the action of t he a erodynamic forces on
the turbine blade.
The blade is analyzed us in g chor dw ise
st ri ps along the span so that two-dime nsional analysis can
be used on e ach e l eme n t .
Overal l
blade forces a nd moments
are obtain e d by summing e l eme nt contribut i on s .
Figure 1
shows a system of forces act in g on a wi nd turbine blade
elemen t.
w'
Th e c omb inati o n of the wind ve l oc i ty , V
the
blade rotational ve l ocity , wr , and induc e d effects , forms
an e f fective or a resu ltan t wind velocity, Vro
This
resultant wind ve l oc ity causes lift an d drag forces on the
b lade element.
Many la r ge scale wind turbines u t ilize
blades with zero pitc h an d zero t wi s t.
For th ese b lades,
the torqu e (Q , positive in the direct i o n of rotation) , is
produced only by the force componen t
in the direction
parallel to th e airfo il chordline , whil e th e thrust (T,
positive in th e d ownstream dir e ction) , i s produc e d only by
the force componen t
chordline .
in the dir ec tion normal to th e airfoil
In nondimensional fo rms ,
t~ e
torque-producing
component is cal l ed ch o rdwise suct ion coeff ici e nt c ' and
s
the thru st- prod ucing compon e n t is cal l ed normal coeff ici ent
Cn ·
The compo nent C
s
i s take n positive in the dir ec tion
toward the lead ing edg e of th4 ai rfoil so that pos itive C
produces pos itive to rq ue.
The component C
n
is d e fined
posit iv e in the pos iti ve thrust (d ownwind) dir ect ion.
8
s
Th e
ma t he ma tica l
re l a ti o nship s b e tween th ese components a nd
li f t a nd d r a g coef ficients ar e :
c
c
where c
l
l
l
sin(Cl )
cas(cx)
+
cd cos(CX)
(1)
Cd si n(a)
(2 )
is t h e t raditional airfoi l sectional lift
coefficient and cd is the traditiona l sectional drag
coefficient.
The e ffe ctive angle of attack, a , is formed
by the resultant wind ve locity and the airfoil chordline
(or th e pla ne of rotat ion for the case of a zero- twis t and
ze ro- pitch wind t urb in e blade).
Since the local tangential
velocity decreases with decreasing radius along the span,
the angl e of at t ack is higher for inboard blade sta tions.
Figure 2 shows the effects of ti p - speed ratio a nd l ocal
blade radius on the local angle of attack.
For a normal
operating tip- speed ratio of about 5 , the ang les of attack
range from approximately 12 to 20 degrees for the outer 50
percent portion of the blade.
The purpose of th e present project is to r e duce the
rotational speed of the wind turbine under no- loa d
conditions.
Studies have shown that for tip-speed rat i o s
of about 0.7 o r less, a sma ll mechanical brake could be
utilized to bring the rotor to a complete stop .
At this
t i p- speed rat i o, th e range of angles of attack is from 60
r
t o 90 d e grees f or all stations alo ng the blade span.
9
Th e r efo r e , s tudi es of airfoi l charac t er istics at very high
a ngl es o f attack ar e essential for s l ow- down analysis of
wind t urbin e s .
FACILITY AND INSTRUMENTATION
All tests were conducted in the 7 x 10 foot Walter
Beech Memoria l Wind Tunnel at Wic hita State Un i versi t y .
Instrumentation consisted of a spec i a l
fo r ce-moment balance
in which a 10 hp variab l e speed, water cooled, var ia b l e
frequency model motor was mounted .
Thi s force bala nc e is
fitted with strain gaged flexu r es so that to rque and thrust
r
can be measured directly.
The motor RPM can be controlled
by means of a var iabl e frequency ex t e rnal excitation
system.
Rotor RPM was measure d by a sig nal generator
mounted internally.
Force da ta a cqu isi tion and processing
were accomplished by the Hewle tt-Packar d Model 2 lMX
mini - computer located i n the tunnel co ntr ol room.
These
force data were corrected using wind tunnel corrections fo r
solid blockage and wake blockage as given in r eference 7.
The rat i o of r otor disk area to tunnel cross- section ar ea
is only 0 .0 321 , making sol id and wake b lo ckage cor recti ons
small .
Traditional wind turbine performance pa rame t ers
were calculated using a data reduction computer program
available in the WSU Walt e r Beech Wind Tunnel.
r
These
quantities were then recorded , tabu l ated and p l otted .
10
Sur f ac e f l o w pa tte rns we r e observed using fluorescent
mini-t uf t s at t a ched to th e s uc t ion (downwind) s ide of the
rotor b l a d e , with illum i nation provided by a 400
watt - s econd s tudio s trobe light with a UV-passing filter
(Corning Glass no. 5970) .
Flow patterns wer e then
photographed by a motoriz e d , remote-control Pentax LX
cam e ra fitted with a 200 mm lens and a Wratten 28 filter;
the camera was fixed to a special tripod located about 10
rotor diameters downstream .
MODEL DESCRIPT ION
Three rotor models were u sed in these tests .
All
three rotors have diameters of 20 inches and chords o f 1 . 75
inches.
These models have airfo il sec tions for all
stations from 21 percent span to the tip.
The h ub sectio n s
are rectangular with rounded edges out to 10 percent span,
with a tapered transition to the airfo il section at 21
percent spa n.
The solidity factor (blade p1anfo rm
area/swept disk area) of these rotors is 0.111.
The first model uses the NACA 23024 airfoil , and the
second model uses the NACA 64 -621 airfoil for stat ion s
3
from 21 percent to the tip .
The third mode l utilizes the
NACA 23024 air f oil , mod i f i ed to incorporate a 30 percent
chord ail e ron at - 90 deg r ees fixed deflection from 70
r
p e rcent s pan to th e t ip .
Th e hingel in e position of the
11
aileron is a t 80 per c e nt along t he chord f rom the leading
edge and 14 perce nt above the ai r fo il chordline .
The
ail e ron-de f lector geom e try and hi ngelin e location wer e
d e termined from airfoil s ec tion tes ts documented in
r e ference 4.
Th e v e nted d ef l e cto r aileron prese nted a
sp e cial challenge for model fabrica ti on because of the high
centr i fuga l loading (700 0 g ' s ) associate d with operation a t
5 000 RPM .
The aileron was fabrica t ed from solid maple (the
sect ion removed by cutting from t he basic planform) .
The
deflecto r was fab ricat ed from a graph i te composite
l am inat e , an d th e a il eron- deflec tor assembly was at tach e d
to the r oto r by a ser i es of graph ite fibers l ooped to form
a tension " be l t " which was bonded in to the main blade to
carry t he centrifugal forces.
Figu r es 3 , 4 and 5 sh ow the
airfoi l sections and ai l eron geometry , and figures 6 and 7
show th e rotor planform geome tr y .
Ordinates for the NACA
23024 airfoil and the NACA 6 4 - 621 airfoil (reference 8 )
3
are g i ven in Append ix A and Append ix S, re spectively.
r
12
RESULTS AN D DISC USS ION
For most tests reported here, rot o r RPM was kep t
constant and tunnel dynamic pressure was va ri ed .
The rotor
RPM va lu es ranged from 600 to 5 , 500 and the t unn e l dynamic
pressure was varied from 1 to as much as 50 psf.
The
purpose of testing at high tunne l d y namic p r e s s ur e a nd low
RPM was to obta i n very low tip- speed ratios.
Test
tip-speed Rey nolds numbers a nd tip-spe e d Mac h numbers are
given in Tab l e 1 .
Results are presente d in terms of
thrust , torque and power coeff i c i e nts as a fu nction of
tip - speed rat i o (TSR ), a n d r oto r powe r output as a function
of wind velocity .
Tabu lated data a r e g i ve n in Append ix D.
Ana l ytical studi es were condu c t ed for most of the
configurations tested using WIND-II, a FORTRAN code fo r
predicting rotor performance (refe r e nc e 5) .
One of the
input requirements for WIND- II is a set of 2-D lift and
drag coefficient data as functio n s of ang l e of att a ck for
the airfoil sec ti on on the r otor .
It i s important to not e
that a ll 2-D data used as i nputs to WIND-II were from tests
of a 9 -i nch chord , 36 -i nc h spa n model which were obtained
at the Reynolds number of 0.6 x 10 6 ( r eferences 2 a nd 9).
Chord Reynolds numbers for the prese n t
tes t s were l owe r,
ranging from 0 . 02 x 10 6 at th e inboa rd sta ti on to 0.11 x
10 6 at the tip for low RPM tes t s .
For high es t RPM tes ts ,
the c h ord Reynolds nu mbe r s range from 0.11 x 10
inboard stat ion t o 0 . 58 x 10 6 at the tip.
13
6
at the
J.
TABLE 1
Test Ti p - Speed Reynolds numbers and
Configuration
T~p - Speed
Mach numbers.
~t
Ret
Maximum
Minimum
Minim um
Maxi mum
NA CA 23024 Rotor
0 . 11 x 10
6
0.58 x 10
6
0.08
0 .4 3
NACA 23024 Rotor with
0.30e Aileron , Gap Open
0 .11 x 10
6
0 . 37 x 10
6
0.10
0 . 28
NACA 23024 Rotor with
0.30e Aileron, Gap Closed
0.11 x 10
6
0.3 8 x 10
6
0 . 10
0 . 28
NACA 64 - 62 1 Rotor
3
0.12 x 10
6
6
0.56 x 1 0
0.09
0.43
Test s of th e Clean NACA 23024 Rotor Withou t Ail eron
r
F i gur e s 11 and 12 present the results of te sting the
NACA 23024 rotor without the a i le ron, and wi thout
transition str ips ( c l ean) .
Since the aerodyna mic
characteristics of a i rfo il s at low Reynolds numbers are
often dominated by laminar sepa ration , t ran s i t i on location
effects we re studied analytically using 2 - D data with 1 , 2
and 3 transition str ips
WIND-I I.
(from r e fer e nce 4) a s in puts to
Resu l ts of these studies are compar ed to
experimental measurements as s hown in Figur e 11.
Figure ll(a ) sh ows the plot of thrust coeffic ient as
a funct ion of TSR fo r the clean NACA 23024 ro to r.
As
predicted by WI ND- I I , th e thru st coefficient of this r o tor
increases with TSR .
Theoretical ca l culations s how that the
case with no transit i on str ip shows t he best agreeme nt with
the experimenta l measu rements , al though all case s show
about the same trend .
The effect s of trans i tion st rips ar e much more
significant on torque coeff i c i e nt than thrust coefficient .
F igur e ll(b) shows plot of torque coef f ic ient as a function
of tip- speed ratio.
Expe rime nt a l data shows that the rotor
state of zero- torq ue occu rr ed a t
the TSR of 1.5 , 4.0 a nd
8.0.
Max imum to rque coeff ici ent occurr e d at TSR of a bou t
5.0.
Theoretical cal culation s wit h .no transition st rip
show a much higher C peak than e xpe rimen tal re sults .
Q
Transition st rips r e duce ma ximum pr e dict ed C "
Q
15
The
anal y s i s based o n 2- D data wit h t hre e t r a n s iti o n strips
produces a bo ut t h e s ame ma x i mum to rque c o ef fici e nt as t h e
c l ean rot o r tes t s .
Powe r ca l cu lat e d an d plot t e d as a function o f wind
v e locity i s s hown in f i gu r es 1 2 (a) thr ough (c) for rotor
RPM o f 20 0 0 , 30 0 0 a nd 4 0 00, r es p ec tiv e l y .
For all thre e
cases , th e oret ical ca l culati o ns from WIND-II over-pr edicte d
th e pea k powe r and the cut-out wind speed for the rotor.
The ana l y si s , however, agr ees v e ry well with the
expe r ime n ta l meas ur e me nts f o r the portion of the power
cur ve f rom t h e poin t of c u t-in ve l ocity to the point wher e
ex p erim e n t a l da t a show s maxi mum powe r is r e ached (blade
s e ct i o n s t al lin g) .
r
One r e ason WIND- II predictions may diff e r from the
rotor e x peri me n ts is t h a t th e a irfoil s e ction data u sed as
in put t o WI ND-II we re f r om te s t s at a Reynolds number of
0 .6 x 10 6 , whil e ro tor Reynolds numbers were s ubstantially
l ower .
It
is re comme nd e d, t he r e fore , that t ests be
co nducted to o btain low Rey nolds number airfoil data f o r
these bla de sect i ons.
The lower Reynolds number airfoil
s e ctio n d a ta shou ld t he n be u sed as input s to WIND-II to
refi n e t h e pr e d icte d pe rf o rmanc e of the rotor blade . The
Mach numbe r d i ffere nces b e twee n non-rotating and rotating
e xper i me n ts are no t c onsi d e r e d s ignificant.
r
16
Tests of the Cl ean NACA 64 - 621 Roto r
3
The test re s ults of the NACA 6 4 - 621 rotor without
3
trans iti on strips are presented in terms of nondimensional
pa r ameters as s hown in F igure 13 and r o tor power output as
shown in F i gure 14.
As shown in Figure 13, theoretica l
calculations are
simi lar to e xpe rime ntal measurements for thrust coefficient
as a function of TS R.
Howev e r , the tests show much lower
maximum to rque an d power coeff i cients than pred icted.
A ve ry
interesting point for th e se t ests is that the NACA 64 -621
3
rotor had o nl y one speed (TSR of 6 . 7) for which torque is
zero , whil e th e theoretical calculations from WIND-II predict
st at es of zero-torque for the rotor to occur at 0.4 , 2 . 0 and
6.7 TSR .
Figure 14 prese nts the results for the NACA 64 -621
3
rotor in terms of power as a f unction of wind velocity.
Similar to the results for the NACA 23024 rotor,
analytical
calculations over-pr ed ict the peak-power , and agree with
e xper im e ntal measurements only from the point of cut-in
velocity to the point of maximum power measur e d
expe rimenta lly .
As wind velocity is increased, however ,
results from this series of tests are no long er s imilar to
those of the NACA 230 24 rotor.
F urthermore, calculations
from WIND- II fa il to predict the cut-out wind speed of the
NACA 64 -621 rotor .
3
Figure 14(a) shows the plot of power as
a f unc t ion of wind s peed for the NACA 64 -621 rotor at 2000
3
17
RPM.
Expe r ime n ta l data s how s that t h e r otor power ou t pu t
r eac h es i t s ma xim um at th e wind speed of a bout 1 3 me t er/sec;
for wi nd speeds gr e at er th a n 13 me te r / s e c, power de c reas e s.
WI ND-I I p r e d i c ted a c u t - o ut wi nd speed for this c a se a t 26
met e r/ sec .
Unl i ke t heor e t i ca l pr e dictions, th e power output
of the NACA 6 4 -6 21 r o to r r e mains nearly c onstan t at positive
3
Due to the
pow e r for wi nd speed fr om 25 t o 29 me ter/ s ec.
ov er s p ee d li mitation on th e wind tunnel · motor - dynamom e ter
sys t em , maxi mum wi nd speed o f the test s wa s restricted t o 29
mete r / s e c .
Al t h oug h t u nnel velocity was limited to only 24
me t e r /sec for the r o tor at 3000 RPM , similar results we re
obtained as shown in Fi gure 14(b).
I n summa ry, t h e WIN D-II pr e dictions based on airfoil
r
section data a r e rea so n abl e fo r low angl e s of attack , but
poor f o r hig h ang l es o f atta c k (high wind speed).
Th e
pres e nt test data ar e c haract er ized by a d istinct peak in the
power ve r sus wi nd speed p l o t, followed by a region of
decreasi ng power , a nd th e n a r e gion in which power i s
r e l atively c o n sta n t wi t h wind speed.
In fact , for th e case
of 20 00 RPM, the measured powe r at high wind spe eds exceeds
t h e WI ND-I I p r edic ti o n.
Rasmus se n (reference 11 ) report e d
results sim i la r to t he prese nt te sts , with power initially
decr e as ing be y o nd peak power , followed by c onstant or
in cre asing power as wi nd spee d i s further in c r e ased.
He
de sc ribe s " a djus t me nt s " to be made to the airfoi l section
da ta t o ma tc h me a s ure d powe r f or the high wind speed
r
cond i t io n s .
NASA Lew i s t es t r esu lts from a larg e - s cal e
18
r
(MOD-OA , reference 12) turbine s how that the power also
exceeded WIND-II p r e dictions at high wi nd speeds .
For th e
MOD-OA rot or , the power reached a maximum , and th en remained
constant for higher wind speeds.
The tr e nds from t h e present
wind tun nel tests of the NACA 64 -62 1 r otor are quite similar
3
to the Rasmussen results , and somewhat similar to the NASA
MOD-OA results .
Performance Comparison Between Th e Two Rotor Mode l s
Figures 15 and 16 compa re the tes t
2 3024 r otor and the 64 - 621 rotor .
3
r esults between the
Ta b le 2 summarizes some
of the performance ch a r acteristics for bo t h r otors .
TABLE 2
Perfo rmance Compar is o n
Model
NACA
23024
Rotor
NACA
64
621
R tor
r
r
TSR at
C p =0
TSR a t
Ma ximum
Cp
Max i mum
Cp
1.5,4.0,
8.0
5 . 18
0 . 1 59
6.7
4 . 40
0 . 1 51
The maximum Cp for th e NACA 64 - 6 21 r oto r is nea rl y t he
3
s ame as that of the NACA 2302 4 rotor , bu t it occurs at a
19
lower TSR .
r
As shown in figure 15(c), the 64 -621 rotor
3
produces high er C p for TSR less t han about 5 but lower Cp for
TSR gr e ater th an abou t 5.
Thi s mea ns that at lowe r wind
speed , the 23024 rotor produces greater powe r, and at high
wi nd , the 6 4 -621 rotor produces g r ea t er power.
3
For the
three RPM se tting s tested , the 64)-621 rotor produces higher
maximum power th an th e 23024 rotor (figure 16).
Effects of Tran s ition Strips on t he Two Rotors
The purpose fo r this test s e ries was to evaluate the
effects of transition strips on rotor performance.
The
transit i on str i ps wer e commercial drafting chart tape.
r
This
t ape is r ead ily av ailable and eas y to apply consistently.
The tape strips wer e attached along the entire span at 5%
chord on the upper surface and at 10% chord on the lower
surface of the rotor.
Tests were conducted on both rotors
with 0, 1, 2 and 3 transitio n str ips (thickn e sses 0.0",
0.005 ", 0.010" and 0.015").
The tape thicknesses are larg e
relative to rotor thickness, but are dictated by the low
Rey nolds number of t he t ests .
The Reynolds number at the tip
6
for these test conditio ns is 0 . 3x l0 •
Figur es 17 a nd 18 p r e s ent th e results of testing the
NACA 2 3024 rotor with 0, 1, 2 and 3 transition strips.
It is
shown in th ese f igur es that transition strips result in small
reduct ions in thrus t coef ficie nt but larg e penalties in
to rque and powe r coeff icients.
With thr ee transition st rips
20
in sta ll e d , t he NACA 2302 4 rotor p r o duced ne gative power f or
a ll tip- s p eed ratios .
Th e r esu lt s of t es tin g the tra n s i tio n st r ips o n the NACA
64 -621 r o t o r are s h own in figur es 19 and 20.
For this
3
r ot or , tran s i t i o n st rips c au se a smal l r educti o n in thrust
c o eff ici e n t a nd al so re lati v el y smal l changes in tor q ue a nd
p owe r coef fici e nts.
With three trans ition st rips installe d,
rotor peak power is reduced from 0.21 KW to about 0 . 15 KW.
Wi th 1 or 2 transition strips installed , howeve r, rotor peak
power is increased from 0 . 21 KW to about 0.2 3 KW.
The
probab l e r e ason for this un e xpect e d behavior is that the NACA
64 - 621 r o tor had laminar se paration on the uppe r surface for
3
th e low Reynolds number tested , and a trip consisting of 1 or
2 transition s trips helped preve nt this separation .
Similar
trends wer e r e porte d by Rasmus se n (reference 11) who showed
that transition s t rips penalized peak power at high RPM (high
Re ynolds number) , but increas e d peak power at low RPM (low
Rey n olds number) .
His tests were on a twist e d rotor with
NACA 63-212 / 24 airfoil sections.
The mo st signi f icant finding from this s e ri e s of tests
is that tran s ition str i ps have a muc h larger penalty on th e
NACA 23024 rotor tha n on th e NACA 64 -621 rotor.
3
That is ,
th e NACA 23024 airfoil is much more sensitive to roughness
than the NACA 64 -621 a ir fo i l .
3
Similar trends were obtained
from 2- D t e sts of the 2302 4 airfoi l and the 64 -618 airfoil
3
6
at Reynolds n umbe r of 0.6xlO , documented in WSU Report
WER-16 (R ef ere n c e 13).
21
F low Visualization
A series of flow vis ualizations we re conducted on the
clean NACA 23024 rotor and the NACA 64 -621 rotor .
3
Surface
flow patterns were observed using fluorescent mini - tufts
attached to th e upper s urface ( suct ion side) from 30 to 90
percent rotor radius at 10 p e r cen t increments along the
b l ade span, with illumination provided by an ultra- violet
strobe light.
Th e tests were conducted at 800 RPM, with
tun n e l dynamic pressure varied from 0 psf (infinite TSR) to
5 ps f
(TSR about 1).
The purpose of these tests, as stated earlier, was to
.
r-
d e term ine the e xt e nt of spanwise f low along the blade .
It
i s believed t hat at angles of attack near stall , spanwise
flow helps del ay separ at ion on the upper su rface of the
rotor , resulting in p ower prediction discrepancies
discussed in preceding sections .
Figure 21(a) shows the p icture of the clean NACA 23024
rot or at infinite tip- speed ratio (0 psf tunn el dynamic
pressure).
The pattern s of the tufts indicate only
chordwise f low for all stations along the blade surface.
Th i s tuft orientation indicates that the tuf t g-load or
c e ntrifugal acceleration do not have a major effect on th e
tufts.
When the tip-spee d ratio was decreased by
incr eas ing the tunn e l wind velocity , spanwise flow began to
develop starting from the inboard stations.
It is shown in
f igur es 21(b)-(i) that as TSR decreased, the region of
22
s panwi se flow e x panded fr om near the root, outboard toward
th e tip o f th e blade.
At a tip-speed ratio of about 1,
spanwis e flow is fully deve lop e d fo r all stations alo ng the
blade span .
Figure 22(a) shows th e NACA 64 -621 rotor at infinite
3
tip-speed ratio.
Similar to the results of the NACA 23024
rotor , tuft patte rns show only chordwi se flow.
At tip-
speed ratio of 5.20 , the inboard 70% portion of the blade
spa n indicates spanw i se flow as shown in Figure 22(b) .
Figures 22(c ) to (i) s how that spa nwise flow bec omes fully
developed over the entire blade span at
tip-speed ratios
less than about 3.
Table 3 summar iz es the results for this se ri es o f f l ow
visualization tests.
If spanwise flow is evidence of blade
stalling, the trend of the 64 - 621 rotor to encounter
3
spanwise flow at lower TSR than the 23024 rotor seems
inconsistent with the torque and powe r measurements which
.
show more pos iti ve torque for the 64 - 621 rotor.
Careful
3
study of airfoil section data for the two airfoils reveals
that while the 64 - 621 airfoil has a lower initi al stalling
3
angle, the stall progressio n is quite slow, and the C
curve is quite flat near the p e ak .
Thus this airfoi l
the ab ility to reta in high l ift eve n wh en substantial
separation is present .
23
l
ha s
J.
")
TABLE 3
Spanwis e Flow Ob se r va ti ons From Tuft Stud i e s
q
Ub/ft 2 )
0.0
...'"
V
TSR
(ft/ se c )
0.0
Ret
M
t
(million)
~
0.0839
0.0625
(@
800 RPM).
Spanwi se Flow
NACA 23024
NACA 6 4 - 6 21
no ne
none
3
0 . 20
13.41
5.20
0.0854
0.0637
Root to 0 .4- R
Root to 0 . 6 - R
0.40
18.97
3.68
0.0869
0 . 0648
Root to 0.5 - R
Root t o 0 . 7- R
0.60
23.23
3 . 00
0 . 0884
0 . 0659
Root to 0.6-R
Root t o 0 . 9- R
0.80
26.83
2 .60
0.0899
0.0670
Root to 0.6 - R
Ro o t to Tip
1.00
29 . 99
2.33
0.0 913
0.0681
Roo t
1.50
36.74
1.90
0.0948
0.0707
Root to
o.8-R
2.00
42 . 42
1.65
0.0981
0.0732
Root to
o.8-R
5.00
67 . 07
1.04
0 . 1154
0.0867
Ro o t
to 0.7 - R
to 0 . 9-R
Tests of NACA 23024 Rotor with 30% Chord Aileron
Figures 23 and 24 present the resul t s o f testing the
NACA 23024 rotor equipped with a vented aileron-deflector
locked in the 90 degree upward pos ition.
Figure 23 shows the compar i so n betwee n the theoretical
pred i ctions from WIND-I I a n d the e xpe rime ntal measu r ements
for the gap-open a ileron co nfiguration.
WIND-I I predicts
approximat e ly 10 % lower thrust coeff ici ents for nearly all
tip-speed ratios greater than 2 as shown in Figure l2(a) .
Figures 2 3( b) and (c) show the plots of torque and power
coefficients, respectively , as a function of tip- speed
ratio .
At tip- speed ratio of less than 3, calculations
from WIND-II show nearly the same resu l ts as those of the
r
.
expe rimental measu r eme nts, espec ially for th e power
coeffici e nts.
At tip- speed ratio of greater than 3,
however , analytical calculations predict both torque and
power coeff ici ents lowe r
(more negat ive) than measured .
i s possible that the di screpanc ies between analysis and
measurement result from the Rey nolds numbe r of the t es ts
being lower than the ana lysis.
results in a low s lope of the c
Low Reynolds number often
l
versus a curve for
airfoils, and this will re s ult in reduced magnitude
(positiv e or ne gative ) suction coeff i cient, and hence in
reduced magnitude (positive or ne gative) rotor power and
torque .
I t i s shown in Figure 24(a) that by leaving the gap
between the a irfoil and the aileron open , the thrust
25
It
coeff i cient i s somewh at l o wer t ha n t hat of th e bas i c NACA
23 0 2 4 roto r fo r TS R fr om 4 to a bou t 8.
Whe n t he gap is
closed , th r ust coeff ici e n t be c omes high e r t ha n th o se of the
bas i c rotor a n d t h e gap- ope n a i le r on c o n fi gur at i o n s , f or
TSR f r om 1 t o a bou t 5 .
At th i s ra n ge o f TS R ( a t high ti p
a ng l es of at tack) , t he gap- c l o sed aile r o n c onf i gu r at ion has
larg e r pr of ile drag a r ea t h a n th e bas ic r otor a nd the
gap- op e n aileron r o t o r c o n fig u r a tions.
At TSR g reater than
5 (at l ow ti p angl e s of a ttac k ), howev e r, t hr us t
coeffic i ent becom e s l owe r du e t o th e loss o f lift c aus e d by
th e upward defl e ction o f the a il e ron.
Figures 2 4 ( b) a n d (c ) show t h e e ffects of th e ail e ron
on torq u e a nd p ower c oe f f i c i e n ts as a func t ion of TS R.
r
Both g a p-ope n and gap- c l osed ai l e r o ns produc e d neg ative
t o rqu e for al l TSR .
Due to tes t l imita tion s , th e l o we st
a c h i e vabl e TSR for the g ap- ope n c onfigura ti o n was 0.65 and
a TSR of 0 . 54 f or the gap-closed configuration.
Th e
gap- op e n ail e r o n configu r a ti o n produc e d larg e r n egativ e
t o rqu e c o e f f icient s tha n the ga p - c los e d co nfig ura ti o n f o r
al l TSR t e ste d (u p to about 8).
In o r der to determ in e the stat e of ze ro-torque f o r
th i s model , the rotor was wi ndmill e d, that i s , the ro to r
was dr iv en on l y by th e t un ne l wi nd v e l o ci ty , for a s e ri es
of t u nn e l dynamic pressures .
The TS R f or the ze r o -to r que
s t ate fo r th e gap- op e n co nf igura t ion wa s fou n d to be -0.6
a nd -0 .7 for t he gap- c l ose d c onfigurati o n.
r
mea n s th at th e r o tor wa s t urn i ng bac kward .
26
A ne gati ve TSR
In addition , a coast-down tes t was conducted for the
gap-open ai l eron co nfiguration .
For th e test , the tunn e l
dynamic pressure was kept at 3 psf , and the rotor speed was
driven to 3000 RPM, which cor r esponds to a tip-spe e d ratio
of about 5.
The electrical power driving the rotor was
then di sconnected, a nd th e rotor b l ade was a llowed t o coast
dow n to an equ ilibrium ze ro-torque state .
It took
approx imately five seconds for th e rotor to dec e lerate f r om
3 000 RPM t o zero RPM and about 2 more seconds to reach the
r eve rse- rotation equ ilibrium state of zero-torque at the
tip-spe ed rati o o f -0 . 6 .
Thus th es e tests ha ve clea rly
demonstrated the abi lity of thi s configuration to protect
against rotor overs peed.
The fact th at the aileron-cont r o lled rotor r es ults in
reverse rotat ion is not an insurmoun t able problem .
Three
soluti o ns are possible:
(1)
Allow the slow reverse auto - rotation .
This
rate i s so l ow that it probably would not
result in damage , eve n in hurricane winds .
(2)
Limit aileron deflection angle to l es s than
90 d e gr ees .
(3)
Reduce the size of the ail e ron chord or
lower surface e xtensio n plate.
It is r ecomme nded that a n ai l eron of this type be
tested at sma ll er angles of d ef l e ction (60 , 70 or
80
d eg re es) o r with smaller extension plate (5, 10 or 15
perce n t c hor d) on the l ower s urface .
27
CONCLUSIONS
1.
The NACA 6 4 -6 21 r otor produces higher peak power
3
than the NACA 2302 4 rotor for a given rotor RPM.
The
NACA 23024 , however , gives more power than the
NACA 64 -621 at l o w wind s peeds.
3
2.
-
Transition strip studies show that the NACA 23024
rotor is ve r y se nsitive to roughnes s and that when
transition str i ps are installed, it suffers a
gre a t e r pe nal ty than the NACA 64 - 621 rotor.
3
3.
r
Surface tufts studies indicate the existence of
spa nwis e f low for TSR of less than or equal to about
1 for the NACA 23024 rotor a nd l ess than or equal to
a TSR of about 3 for the NACA 64 -621 rotor.
3
4.
Analytical studies from WIND-II consistently over-
pr ed ic ted maximum power for the two clean r otor
c onfigurations.
The predictions, however, show very
good results for operation at low wind speeds (high TSR).
5.
For the purpose of loss-of - load control, the aileron
configurati o n tested for this proj ect is capable of
producing mo re than e nough ne gative torque to prevent
overspeed.
r
The unloaded rotor with a ileron will
rotate backward at a tip- speed ratio of - 0.6.
28
RECOMMENDATIONS
1.
Tests should be conducted to obtain low Reyno lds
number airfoil data for these blade sect ions , and
these data shou ld be used to check the analytical
model.
2.
The vented aileron - deflector configuration tested in
this project should be evaluated on a full - scale wind
turbine machine where much higher Reynolds numbers
exist .
3.
The aile ron of this type should be tested at smaller
angles of de flec tion (70 and 80 degrees) or with
smalle r extension plate (5 , 1 0 and 15 percent chord)
on the lower surface to reduce negative rotation rate.
29
REFERENCES
1.
Wentz , W.H. , Snyder , M.H . , and Calhoun , J.T.,
" Feasibility Study of Aileron and Spoiler Control
Systems for Large Horizontal Axis Wind Turbines , "
NASA CR-1 59856 , DOE/NASA/3277 -1 , WER - 10 , NASA Lewis
Research Cente r, t-Iay I 1 980 .
2.
Wentz , W. H. , Snyder , M. H., and Cao , H. V., "Eff ects of
Spo i ler Hinge!ine Location o n the NACA 23024 Airfoil , "
(Unpublished Interim Repo r t ) WER - 27 , Wind Energy
Laboratory , Wichita State Univ e rsity, August , 1 9 84.
3.
Trainer , A. G. , " Overspeed Control of Horizontal Axis
Wind Turbines Using Spoilers ," M. S . Th esis , Wichi ta
State Univers i ty , May , 1984 .
4.
Snyder , M.H., Wentz , W.H ., an d Cao , H.V ., "Additiona l
Reflection Plane Tests of Control Device s on an NACA
23024 Airfo i l , " (U npubl i s h ed Interim Report) WER- 26 ,
Center for Energy Studies , Wichita State University ,
February , 1985 .
5.
Snyder, M.H ., and S ta ples , D. L ., " WIND- II Users
Manual, " (Unpublished Inte ri m Report) WER- 15 , Wind
Energy Laboratory , Wichita State University , July ,
1982.
6.
Cao , H.V . , " Performance a nd Aerodynamic Braking of
a Horizontal - Ax is Wind Turb ine from Small-Scal e Wind
Tunnel Tests ," Maste r of Sc i ence Thesis , Wichita State
University, May , 1985.
7.
Pope , A. , and Harper , J . J . , Low Speed Wi nd Tunnel
Testing , John \viley and Sons , Inc ., New York , 19 66 .
8.
Abbott , I.H. , and Von Doe nh off , Theory of Wing
S ect ion s , Dover Publicat ion , 1958 .
r
30
r
9.
10 .
11 .
S ta ples , D.L ., and We ntz , W.H., " Analyt ica l Stud i es
of Aerody nam ic Braking and Control of t h e Mod-O Wind
Turbine wi th a 38t- Chord Ve nted Aileron on an NACA
64 1 -621 Tip Sect i on ," (Unpublis hed Interim Report)
PIP-I 3, Wichita State Univers ity , February , 1985.
Wentz , W. H., Ostowar i , C . , Ma nor, D. , and
Snyde r, M. H. , "Horizontal Axis Wind Tu rb in e Wake and
Blade Flow Meas ur eme n ts from Model Tests ," ( Unpublish e d Int er im Repo r t ) WER-24 , Wind Ene rgy Labo rat ory ,
Wichita State University, June 1 98 4.
Rasmu sse n, F .,
" Aerodyn amic Performanc e of a New LM
1 7 . 2 m Rotor ," Twe l th Meeting of Experts - Ae rodynamic
Calculational Met hods f or WEeS , l EA , Cop e nhagen ,
Octobe r 29 - 30 , 198 4 .
r
12 .
Vi ter na , L.A. , a nd Ja n et zke , D.C., "T heoretical and
Experimental Power f r om a La rg e Horizontal-Axis Wind
Turbine, " NASA TM 82944 , Sep tember , 1982.
13 .
Snyder , M. H., Wentz , W. H. , and Ahmed A., "TwoDi mensional Tests of F our Airfo ils at Angles of
Attack f rom 0 to 36 0 Degr ees ," (Unpublished Interim
Report) WER-l6 , Wichita State University , Februar y
19 84.
31
Resulta nt
/
/
Cl
/
/
/
/
/
Cn
,\
I \
\
\
\
\
\
\
\
\
\
\
\
\
\
\
\
w
\
N
wr
Figur e 1
Cd
I
Cs I
Fo rc es o n a wind turbine b l ade e l ement
r
VT -
C
iIIr
.---~
VT/VW
90
0
80
"
(deg)
0.5
60
r
1
40
2
20
5
10
o
o
0 .2
0. 6
0. 4
0.8
1.0
r /R
Figure 2
Effects of Tip-Speed Ratio on Angl e s of Attack
as a Function of Blade Rad ius.
33
...w
Fig ur e 3
~
NACA 23024 airfoil s ection
w
'"
Figure 4
NACA 64 -621 Airfoil Section
3
T
+
-----
w
m
-------Figure 5
NACA 23024 Airfoil, c
Hingeline:
x
=
=
---
-- -------.--
1.75 in., 0a = -90 d e g .,
D.SOc , z = O.14c, O.20 c Extensi o n P l a t e.
- 11.75
r-NACA 2 3024 Airfoi l
Cho rd - 1 . 75 in.
Sec tio n
/I.. -
II.
10 . 0
j
I
A
NACA 6 4 ) - 621 Ai rfoil
Chord - 1 . 75 in.
A
Sec ti o n
2.1 0
tapered
V
L
1.
11
t ransitiDn
2 PLCS
0. 13
TYP .
1.0
r
-0
r
'diU '~
4
P LeS
I
I
B
B
l__.______J~}
Section
20 . 0
A - A
rA
B - B
~
A
* * Al l dimensions are i n inches
•
Figure 6
Rotor Geometr y
37
-i
1. 75
r--
1. 0
L
C :>
10. 0
I
!lACA 230 24 Airfoil
Cho rd . 1.75 in.
I
A
Section
A
2. 10
V
L
L
O. ll
TYP .
1.0
-0
t ape red
t ra n. i ticn
2 PLCS
•.~;;;;
r
11
'. ----1'1
7S
,. __)}o
P- -.
B
A - A
B
Section
B - B
20 . 0
c
rc
I
NACA 23024
Ai r f o il. e - 1.75 in.,
Hi nge line:
x • O. BOe , ~ - O.14 e .
6 a • - 900, O. ZOe Ex t ens i on Plate .
C
Section
I
C - C
* All dime nsions are in inches
r
Figu r e 7
NACA 23024 Rotor with O.30 e Aileron
38
Tunne l Cei li ng
Wind Tunnel Test Section
...
20· OI A.
J
r
Str eamli ne Strut
(1 . 5" thick x 3 .3" c hord )
4" Dl:",
-
PIPE
Figure 8
Test Set-u p
39
Tunnel Floor
Figure 9
Tunnel Test Section (View Looking Upstream)
r
Figure 10
Side Vi e w of the Thr ee Rotor Mode ls
40
r
4.00
3.50
EXPERIMENT,
CLEAN
THEORY - Wl..,2.. ClEAN
THEORV - WlNOZ. 1 T6
3.00
THEORV - WINDi. 3 T6
THEORY -
wnez.
2. T6
2.50
2.00
r
I. SO
I. 00
0.50
0.00
o0
2.0
6.0
4.0
8. 0
10.0
12.0
-0.50
(a) Thru st Coefficien t
-I. 00
r
F i gu r e 11
Eff e cts of TSR on the Clean NACA 23024 Rotor.
41
I!J
0.10
EXPER IWENT #
THEORY - WlNOZ.
THEORY - WINDz.
THEORV - WINeZ •
THEORY - WINDZ,
CLEAN
ClEAN
I TO
• T&
3TS
0.08
Co
0.06
0. 04
0. 02
0. 00
8.
,\/ 0. 0
12.0
''l~
-0 . 02
\
I!J~
\,
'\
\ \ 'I!l1!J
\\
-0 . 04
,
\
-0. 06
-0 . 08
- 0. 10
(b) To rqu e Coe ffici e nt
F ig u r e 11 Continue d
r
42
r
!!I
EXPERIMENT,
CLEAN
THEORY - WIM>Z. ClEAN
0.50
THEORY - WINOI. I TS
THEORV - WJNDZ.
Z TS
THEORY - WI..,.. • T6
0.40
--,
Cp
/ , "\
I '
\
0.30
I '
I ,'
\\
/'/' /"\\
0.20
\
/'
/
/'
f/
t //
0. 10
d1J.--\
/
\ \
!!I
\
\
!!I!!1% \. \ \
'l!!\ .\\ \\
" /!!1
0.00 +1_
\
'7'
,
r--'r--,-----,
o0
8.0
8. ,~
12. 0
.. 10.0
\!!1 '\
'L'\
\l!I'
,
~
-0. 10
'. \
,\
'\
'\
\
,
-0.20
\ \ !!I,\
,\
'\
,
\,\
-0.30
,\
,
'.\
\
-0.40
\, \
\\
-0.50
r
!!I
!!I
(c ) Power Coef fi c i e nt
Figure 1 1 Concluded
43
,
\,
\
r
0. 24
EXPEPIlMEHT,
CLEAN
THEORY - WINDZ ,CLEAN
(!)
0. 20
POWER
(KW)
0. 16
•
o. 12
,
•
0. 08
r
0.0 4
,
,
0. 00
0 6
-
,[!J
I o. r!!l [!J 1!J1Dl!Jm 1!¢10. 0
,
40 . 0
50.0
80.0
V'W(IIIS)
,
-0 . 04
-0 . 08
-0 . 12
•
\
-0 . 16
r
F ig ure 1 2
•
•
( al w = 2 000 RPM
Ef f e ct s o f Wi nd Speed o n Rot o r Powe r for t he
NACA 23 02 4 Rotor .
44
0. 60
I!l
eXP EflIMEHT
I
CLEAN
TtEOfIIy - WlfC)Z,CLE'AN
0. 50
POWER
(KW)
0. 40
,
,
•
0.30
0. 20
O. 10
,
I!l
+--__,:,.'--.-o1e...-...
0.00
o~
.0
20. 0 I!l
50.0
0. 0
80.0
v WCWS)
-0. 10
-0 . 20
-0 . 30
,
,
-0 . 40
(bl to = 3000 RPM
Figu r e 1 2 Contin ued
45
I. ZO
EXPERIMENT,
CLEAN
THEORY - WI NJZ...CLE'AN
I. 00
POWER
,-
(KW)
-
,
0.80
,
0. 60
O . ~O
'!!J !!J
r
O. ZO
,!!J
,
0.00
o~
-M · O
!!J
!!J
!!J!!J
, '!!J
ZO. O
30 . 0
V W(WS)
-0. ZO
-0 . ~o
- 0.60
- 0. 80
r
(c) w = 4000 RPM
Figure 12
Conclude d
46
~ O .O
•
500,0
60.0
4.00
I!I
3.50
CT
EXPER1WENT
THEORV (WIND-II)
THEORV (WIND-II)
THEORV (WIND-II)
0'1'5
THEORV (WIND-II)
.16
o
T6
I T6
• T6
3.00
l . 50
l . OO
I. 50
I. 00
0. 50
0.00
o0
Z. O
4. 0
6.0
1. 0
10 . 0
IZ . O
-0 . 50
-I. 00
r
Figure 13
(a)
Thrust coeffici e nt
Effects of TSR o n th e NACA 64 -6 21 Rotor
3
47
0. 10
I!!
EXPERIMENT
OTS
o TS
THEORY (WIND-II)
THEORY (WIND-lI)
I TS
Z TS
THEORY (WIND-lI)
3TS
THEORY (WIND-lI)
0.08
CO
/'),
-
0.06
/, \
I, "":"\
Ii. ,'-- ' \
1' /
t'I
I.~ !!II!! \
f"
I!!
~
I,ll cP I!!
0. 04
O. Oz
f/
~
r
,
I!!
!!I
0.00
o0
~.
4.0
8.0
VT / Vw
-O.OZ
\~
~.\I!! I!J
"Z~.+,.
-0. 04
\,
\'\
\
-0 . 06
-0.08
- 0. 10
10 . 0
8. 0
(b) Tor q ue Coe ffici e nt
Fig ur e 1 3 Continue d
48
I!!
I Z. 0
0 .50
!!l
EXPERIWENT
THEORY
THEORY
THEORY
THEORY
0 .4 0
OTS
(WIND-II)
(WIND-II)
(WIND-II)
(WIND-II)
OTS
I TS
ZTS
3 TS
Cp
0.30
j':);
(/~
0.20
1.//
ID[!J
f, ,
f/
f/ C!bJ
0'I rJ'!!l1
O. 10
r-
~
I1!J
'I!l
0 . 00
o0
4. a
2.0
VT /
-0.10
-0 . 20
,8.0
Vw
8. 0
~
10.0
~\!!l
~,I1!J
.~
)
!!l
~~
-0 . 30
.~
\\
\\
-0 . 40
-0 . 50
Power Coefficient
Figure 13
Concluded
(c
r
!!l
I
49
\~
!!l
12.
a
,0. 24
a.E'AN
THEORV - WINDZ, CLEAN
EXPERIMENT,
(!)
0.20
POWER
(KW)
0.16
0. 12
,
,
0.08
r
0. 04
!!l
•
I!ll!l •
I!l
1ilJ!l!!l1!l
0.00
o~
-
l!J
10.0
30.0
20.0
Vw
,
-0.04
,
-
40.0
50.0
80.0
(WS)
,
-----
-0.08
-0 . 12
(al
w = 2000 RPM
-0 . 16
r
F ig u r e
14
Eff e cts of Wind Speed on Rot o r Pow e r for the
NACA 64 - 621 Rotor .
3
50
0.80
I!l
EXPER1WENT ..
THEORY -
wnc>z ..
CLEAN
CLFAN
O.SO
POWER
(KW)
0. 40
•
0. 30
0.20
,
,
,
,
I!l l!l
• I!ll!l
I!I
0. 10
ID
0.00
o0
-M' O
20.0
30. 0
SO.O
-0 . 10
,
,
,
-0.20
-0 . 30
-0 . 40
(b) '" = 3000 RPM
Fig ur e 14
Continued
r
51
80.0
r
I. 20
I!J
, CLEAN
EXPERIMENT
THEORV - WINDZ , CLEAN
I. 00
POWER
(KW)
0.80
,
,
-- , ,
,
,
0. 80
I!J'
,
,
0. 40
r
I!J,
0.20
I!l
0.00
o0
--
20.0
30.0
40.0
SO.Q
80.0
-0 . 20
,
-0.40
-0.80
-0.80
(el w = 4000 RPM
Figure 14
Concluded
r
52
,
,
~ . OO
3.50
Cr
I!J
NACA U OZ4 ROTOR
(!)
w.cA 84-3, 82 1 ROTOR , CLEAN
, CLEAN
3.00
l. 50
l. OO
I. 50
(!)
I!J
I!JI!J
I. 00
0. 50
0. 00
o0
2. 0
8.0
~.O
1. 0
10.0
12. 0
-0 . 50
(a) Thrust Coefficient
-I. 00
r
Figure 15
Performance Comparison betwee n the NACA 23 0 2 4
Rotor a nd the NACA 64 -621 Rotor.
3
53
r
0.10
0.08
NACA 2.3024 ROTOft
, CLEAN
NAtA '4.1-'21 ROTOfI, CLEAN
Co
I
0.06
0.04
GI (!) IiII
(!)
(!)
(!)
O.Ol
(!)(!) (!)
(!)!JI!]
(!)
I!]
r
I!]
\%~
0.00
'. 0
Vr / V.
-O.Ol
~
~
(!)~
10.0
11.0
I!]
.
I!]
(!)(!)
I!]I!]
(!)
-0.
(!)
(!)
-0.
-0.08
-0. 10
r
(b) Torque Coefficient
F igur e 15 Contin ued
54
r
0.50
MACA ZlOU ROTOR
, CLEAN
NACA '4. 1-'2.1 ROTOR, CLEAN
Cp
0.30
o.zo
o. 10
r
0.00 1 -_ _
o
-0. 10
IZ.O
10.0
I!l
I!l
I!l
-0. ZO
I!l
(!)
(!)
-0 .30
I!l
(!)
-0.40
-0 . 50
(e)
Power Coeffic i e nt
Figure 15 Conc luded
55
I!l
r
0. 80
, CLEAN
l!l
HAc.-. 23 0 24 ROTOR
(!)
NAC.'. ... - 3-8Z I ROTO,. , CLEAN
0.10
POWER
(KW)
0.60
0.40
r
0 .30
0.20
0. 10
(!) (!)(!)
(!)
(!)
(!)
~
0. 00
o0
5. 0
(!)
(!)
(!)
(!)
l!l25% l!l
10 . 0
Vw
-0. 10
(a) ' "
(!)
(!)
30 . 0
(WS)
= 200 0 RPM
-0 . 20
r
Figure 16
Power Comparison between t he NACA 23024 Roto r
a nd the NACA 64 - 62 1 Roto r.
3
56
r
0. 80
I!)
(!)
~
13 0Z4 ROTOfII
, CLEAN
NACA " -3-'21 ROTOR, CLEAN
O. 70
POWEA
(KW)
0. 60
0. 50
0. 40
0. 30
(!)
0. 20
(!)
(!)
(!)
I!l
(!)
O. 10
I!l
I!l
(!)
0. 00
o0
5.0
~O.O
15 . 0
\
Vw
- 0. 10
-0. 20
20.0
(b)
W
= 3000 RPM
Fi gu r e 16
57
CWS)
Contin ued
I!lz 5. 0
I!ll!l 30.0
r
0.80
(!]
N,Ac,t. 23 024 ROTOR
~
NACA '''-3-'2 1 PlOTOft, CLEAN
, CLEAN
0.70
POWER
(KW)
0. 60
0.50
0.40
0.30
I!l
I!l
(!)
0.20
I!l
0. 10
I!l
(!)
I!l
I!l
I!l
I!l
0.00
o0
5.0
10 .0
I!l
-0.10
-0 . 20
r
15.0
(!)
Vw
20.0
(MIS)
(!)
(el '" = 4000 RPM
Figure 16
58
Concluded
25.0
30.0
SYt.1
4.00
on
I n
to
EXPERIWENT
EXPER 1WENT
EXPEA1WEN'T
+
&XP&AlIoIENT
.n
on
[!J
(!)
3. S0
THEORV
THEORY
THEOAV
THEOfIV
CT
(CLFANl
• T.
(WIND-H)
(WIND-H)
(WIND- I I)
(WIND-II)
I T.
• T.
.n
3.00
2. S0
2.00
r
I. SO
I. 00
O.SO
0. 00
o0
2. 0
8. 0
4.0
8. 0
10. 0
12. 0
-0.50
-I. 00
(a) Thrust Coefficient
Figure 17
Ef fects of Transition Strips on the
NACA 23024 Roto r at 3000 RPM.
59
SYII
0.10
I!J
EXPERIMENT
EXPERI.-ENT
EXPERIMENT
(!)
,..,
0. 08
I
I '
//
0. 06
/.
/.
"
.• .
i/
0.04
.I(
./
r
'/ /
• TS
a TS
EXPERlllEtlT
THEORY (WINO-II)
THEORY (lfINO-II)
THEORY (WINO-II)
THEORY (WINO-II)
'\
'\
\
• TS
I TO
on
an
./""""\ \
I!J
.. /
·Ii ,/
I TS
\
•
"
+
\
(
Co
0.02
t.
• TI (CLEAN)
/'
~\\
,/'--' .
(!)
l!}
"\
\\\
&\
t.
\
\
\\ \
\
\
0. 00
12.0
8. 0
-0.02
+
+
+
-0 . 04
,
\
-0 . 08
- 0.08
-0.10
r
(b) Torqu e Coeff i c i ent
Figur e 17 Continue d
60
,.
SYIA
0.50
I!l
6
+
0.40
EXPERIMENT
I , _\
/ '
0.30
THEOAV (WIND-II)
THEOAV (WIND-II)
\
/ '
TS
OTS
• TS
OTS
I TS
o TS
.TS
I
THEOAV (WIND-II)
THEOAV (WIND-II)
-,
Cp
o TS (CLEAN)
eXpeAllE1lT
EXPERlMENT
eXPERlMENT
(!J
\
1'
1'
\
I: /" \
0. 20
I,
I'
/
\
/'
f /
.t /
0. 10
\ \
/
,C}'--\ \ \
(!J\
I!l
(!)
\
\\ \
\
\
~
0.00
o0
It>
8.0
+
\
,,10 .0
\ (!J
- 0.10
+
+
,\
'\
\
'\'
(!)'
\, \
~
,\
'\
\
-0.20
A'
\, \
-0.30
+
-0 . 40
- 0.50
(e)
Powe r Coeff i cient
Figure 17 Concluded
61
'\
'\
'\
\
'\
'
,
\\
12. 0
r
0.3S
!!I
,
(!)
T6
•
+
POWER
T6
•
A
0 . 30
T6 (CLEAN)
0
T6
(KWI
O.ZS
O. ZO
O. IS
!!I
O. 10
(!)
!!I
O. OS
!!I
(!)
(!)
(!)
(!)
A
A
0. 00
0 0
S.O
(!)O . O
lS . 0
r!f.S'i
(!)
Vw (A/S)
A
-0 . OS
ZOl
(!)
+
I't. ~O . 0
(!)
+ +
+
+
+
+
- 0. 10
+
+
+
-0 . IS
,r
Figure 1 8
Effect s of Tran s ition Strips on Rotor Powe r
fo r th e NACA 23 024 Rotor @ 3000 RPM
62
SYIA
4. 00
I!J
EXP ERIMENT
on (CLEAN)
(!)
EXPERIMENT
t>
EXPERIMENT
EXPERIMENT
THEORY (W1ND-11)
THEO/IY (W1ND-1 1)
THEORY (W1ND-Il)
THEO/IY (W1ND-Il)
I T6
T6
• T6
o T6
I T6
+
3. S0
CT
t
tn
.n
3.00
2.S 0
2.00
r
,.-
I. SO
,.-/,p'
/~,.-
J;:--;/
/ f~-
I. 00
;-
O. SO
~
0. 00
o0
2. 0
1. 0
' .0
10.0
12. 0
VT I Vw
- O. SO
(a) Thrust Coe ffic i ent
-I. 00
r
4. 0
Figu r e 19
Effects of Transition Strips on the
NACA 64 -621 Rotor at 3000 RPM
3
63
SYIol
0. 10
[!J
EXPEftlWENT
EXPE"UENT
OTO (CLEIIN )
(!)
6
EXPE~IIENT
.TO
.TO
o T.
+
0. 08
I TO
EXPE~IWEtIT
THEORY (lUND-II)
TNEOOY (WIND-II)
CO
(WIND-II)
THEORY (WIND-II )
THEOliIV
/).
0. 06
I TO
• T.
• TS
I. \
I· ~
Ii. ..... '\
r/
!'I
I.,1.' !!I6t!i \
0. 04
~+i
+
+
~f.l
0. 02
f'
r
",
0. 00
o0
~.
4.0
8.0
Vr / V'll
- 0. 02
'i-
8. 0
10. 0
\"~1
~,
-0 . 04
'\
\'\
\'\
\
-0.06
- 0. 08
-0 . 10
(b) To r q u e Coef fic i e nt
Figu r e 19
64
Co nt inu e d
12. 0
SYM
0. 50
I!J
eXflEIUMENT
(!)
EXP!Rlwetn'
EXPER1MENT
EXPERIMENT
THEOfIV (WIlli-II)
THEOfIV (WIlli-II)
THEOIIV (WIlli-II)
THEOIIV (WIlli- II)
A
+
O. 40
Cp
0.30
65
OTS
I TS
lTS
3TS
OTS
ITS
2TS
3 TC
( C LEA N )
0. 3S
I!l
0
(!)
I
•
A
0. 30
+
POWER
3
T6 (CL EA N)
T6
T6
T6
(KW)
0. 2S
I!I
~
0. 20
I!l
A
o. IS
+
A
(!)
I!l
~
(!)
A
I!l
(!)
(!)
A A
+
+ + + + +
I!l
<%
0. 10
+
O.OS
0.0 0
o0
S.O
10. 0
IS. O
20 . 0
2S . 0
30. 0
~
-0 . OS
+
-0 . 10
- 0 . IS
F i gu r e
20
Effec ts o f Tr a nsit i o n St r i ps o n Rot or Powe r
fo r t h e NACA 64 -621 Rotor @ 3000 RPM
3
66
r
r
(Rotati on directi on i s clockwise ,
f low directi on i s toward observer . )
(al
Fi gu r e 21
q
=
0 psf , TS R
=
00
Effects of Spanwise Fl o w on th e
NACA 23024 Rotor at 800 RPM
r
67
(b)
q = 0.2 psf, TS R = 5 . 20
F igu r e 21 Con t inu e d
r
( e)
q = 0 . 4 psE , TSR = 3 . 68
Figure 21 Continued
68
(d)
(e)
q = 0 . 6 psf , TSR = 3 . 00
Figure 2 1 Cont inued
q = 0.8 p s f , TSR = 2.60
Figur e 21 Continu e d
69
(r)
(g)
q = 1.0 psr, TSR = 2 . 33
Figure 21 Continued
q = 1 . 5 psr , TSR = 1 . 90
Fi gure 21 Continu ed
70
(h)
( i)
q = 2 . 0 psf , TSR = 1.65
Figure 21 continued
q = 5 . 0 psf , TSR = 1 . 04
Fi gure 21
Concluded
71
r
\.
""""""'
{- ("........
(-£-l.0w d ire cti o n is clockw is e)
(a)
Figure 22
a.,~
. . . Lt·" ...
,'I
Lo"",_",
, t.~~
)
q = 0 psi, TSR = 00
Effects of Spanwise Flow o n the
NACA 64 -62 1 Rotor at 800 RPM
3
72
(b l
r
(e )
q = 0.2 p s f, TSR = 5 . 20
Figure 22 continued
q = 0 . 4 psf, TSR = 3.68
Figure 22
73
continued
(d)
q ~ 0 . 6 psf , TSR ~ 3 . 00
Figure 22
Continued
r
r
(e )
q ~ 0.8 psf , TSR ~ 2 . 60
Figur e 22 Cont inu e d
74
(f)
(g)
q = 1 . 0 psf , TSR = 2 . 33
Figure 22 continued
q = 1 . 5 psf , TSR = 1 . 90
Figure 22 continued
75
I~
(h)
q = 2 . 0 psf , TSR = 1. 65
Fig ure 22
Continued
r
(i)
q = 5 . 0 psf , TSR = 1 . 0 4
Figure 22 Conc l uded
76
r
4.0 0
3. 50
EXPEAlYENT
, CLEAN
THEORV
, CLEAN
J
3. 00
2. 50
2. 00
r. 50
I!)
r. 00
~
I!)
I!)
-IlIIDIIIJ
I!) I!)
/~'
0.50
,
0.00
o0
2.0
8. 0
4. 0
- r. 00
r
F igu re 23
10. 0
12.0
VT I Vw
-0 . 50
\
8. 0
(a) Th r us t Coefficien t
Effec ts o f TS R on th e NACA 2302 4 Rot or wi t h
th e 30 % Cho rd Ail e ron a t Gap - Ope n position.
77
r
0. 25
EXPERIMENT
0.20
THEORV
Co
, CL EAN
, CLEAN
0. 15
o. 10
0.05
r
0.00
8. 0
4.0
-0.05
B.O
VT / Vw
·19
• [!J
[!J
-0.10
-0.15
[!J
[!J
[!J
@
[!J
[!J
-0.20
-0.25
r
( b ) Torque Co effic i e nt
F i gure 23 Co n t inu e d
78
10.0
12.0
r
2. 00
1. 60
EXPERIMENT
THEORV
Cp
, CLEAN
, CLEAN
I. 20
0. 10
0. 40
r
0. 00
o0
4. 0
,
-0 .40
-0 . 10
8. 0
1. 0
VT I Vw
, I!l
, I!l
, ~
lID
I!l
I!l
-I. 20
I!l
-I. 80
\
-2.00
(e ) Power Coe ffici e nt
Fi gur e 23 Concluded
79
10. 0
12.0
4. 00
3.50
CT
6a
GAP
I]
NACA U02.4 ROTOR
D.D
(!)
NACA 23014 "OTOII
-'0.0
NONE
OPEN
!;
NACA 23024 ROTOR
-'0.0
ClOSED
3.00
2.50
2.00
I. SO
I. 00
0. 50
0. 00
o0
2.0
4. 0
8.0
•••
10.0
12 . 0
-0.50
(a) Th r ust Coefficient
-I. 00
Figure 24
Effects of TSR on the NACA 23024 Rotor as a
Fu nction of Aileron Gap positions.
80
r
0.25
0. 20
CO
°a
GAP
NONE
I!l
NACA 110 24 IIO'TOA
0.0
(!)
NACA Zl OZ4 ROTOR
NACA Zl OU ROTOR
- '0. 0
Of'EN
-'0.0
ClOSED
A
o. 15
o. 10
81
r
t.OO
6a
I. 60
Cp
I!I
<!l
IJ.
0. 0
NACA 2IOZ4 JIO'I'OR
NAc,t. U O U _
-'0.0
NACA 2.1014 ROTOR
-'0.0
GAP
NONE
OPEN
CUllED
I. to
0.10
0.40
IIIl
r-
0.00
4. a
' .0
lTlJ.
-0.40
Vr / Vw
(!)6~
~ IJ.
•
-0. to
~
- I. to
<!l
IJ.
<!l
- I. 10
IJ.
-t. OO
r
(el Power Coef ficient
Figure 24 Concluded
82
I!I 10.0
I!I
It . O
I!II!I
r
Appendix A
23024 Ai r foil Coordinates
NACA
Upper Surface
Station
Lower Surface
Ordinate
Station
Or dina t e
0.0
0.0
0.0
0.277
4 . 017
2.223
-3.303
1.3 31
5.764
3 . 669
-4.432
3.853
8.172
6 .14 7
-5.862
6.601
9 . 844
8.399
- 6.860
9.432
11.049
10 . 577
-7.647
15 . 001
12.528
14 . 999
-8 .852
20.253
13.237
19 .7 47
-9.703
25 . 262
13.535
24 . 738
-10 . 223
30.265
13.546
29 . 735
-10.454
40.256
12. 928
39.744
-10.278
50.235
11. 69 0
49 . 766
-9.482
60.202
10 . 008
59 . 798
-8.242
70.162
7.988
69 . 838
-6.664
80.116
5.687
79 . 884
-4.803
90 . 064
3.115
89 . 936
- 2.673
95 . 036
1. 724
94 . 964
-1. 504
100 . 0
0 . 252
100.0
0.0
-0.2 52
.* Station and ordinate s given in per cent of airfoil chord.
Al
r
Appendix B
NACA 64 -6 2 1 Air f oil Coo rdinat e s
3
Up pe r Su rfac e
Stat i on
Lower Surface
Station
Ordinat e
Ordinate
- 0 . 085
0.768
- 0.085
-0.038
1. 223
0.0
0 . 08 3
1.696
0.459
-0.954
0. 58 1
2.573
1. 569
-2.006
1.197
3.298
3.096
- 2.851
7.0 4 5
7 . 260
8.455
- 4 . 657
9.294
8.277
10 . 706
- 5 . 173
1 5 .343
10.401
13.68 8
- 5 . 741
21. 43 2
11. 907
19.616
-6.577
24.4 8 6
12.475
25 . 514
- 7.105
30.6 0 6
13 . 276
31. 394
- 7.364
39 .7 9 8
13 .623
40.202
- 7.196
4 8 . 982
12.840
49.018
- 6 . 223
58 .1 2 4
11. 29 6
60.841
- 4 . 268
70 . 2 2 4
8.446
69 . 776
- 2.61 2
79.221
5.944
78.779
- 1.037
88 .152
3 . 353
87.848
0. 1 5 1
9 4.076
1. 665
93.924
0 . 502
100.0
0.0
100.0
0.768
0.0
0.0
** S tation and ordinat e s give n in per c e nt of airfoil chord.
A2
APPENDIX C
Tip-spe ed Rey no lds num ber and tip- speed Mach
numbe r a s a function of tip- speed ratio .
(a
v
l
800 RPM
TSR
(mi l lion)
(ft/seel
**
Ret
0.20
13.41
5.20
0.0854
0 . 0637
0.40
18.97
3.68
0 . 0869
0.0648
0 .60
23 . 23
3 . 00
0.0884
0 . 0659
0.80
26 .83
2.60
0 . 0899
0.0670
1.00
29 . 99
2 . 33
0.0913
0.0681
1.50
36.7 4
1. 90
0.0948
0.0707
2 .0 0
42.42
1.65
0 . 0981
0.0732
3.00
51. 95
1. 34
0 . 1045
0.0779
4. 00
59.99
1.16
0.1106
0 . 0824
5 . 00
67.07
1. 0 4
0.1154
0.0867
Velocities , ti p- speed Reynolds numbers a nd tip-speed
Mach numbers were cal culated a t the tunnel temperature
of 75 degree s Fahrenheit and barometric pres s ure of
28.8 1 ineh Hg.
A3
AP PEN DIX C
(b )
q
!lb/ft2 )
**
v
Continued
1000 RPM
TS R
(ft/sec)
Ret
(million)
1.00
29.99
2.91
0.1109
0.0827
2 .00
4 2 .4 2
2 .06
0 . 1166
0.0869
3.00
51.95
1.6 8
0.1220
0.0910
4.00
59 . 99
1.45
0.1272
0 . 0949
5 .0 0
6 7.07
1. 30
0.1312
0.0986
6.00
73 . 47
1.19
0.1347
0.1022
7.00
79 .36
1.10
0.1381
0.1057
8.00
84 . 84
1.03
0.1414
0.1090
9 . 00
89.98
0.97
0.1445
0.1123
10.00
94.85
0.92
0.1475
0.1154
Veloc ities, tip- speed Reynolds numbers and tip- speed
Mach numbe rs we r e calculated at the tunn el temperature
of 75 d eg rees Fahrenheit and barometric pressure of
28.8 1 i nch Hg.
A4
APPENDIX C
( c)
q
(lb/ft 2 )
**
v
Continued
2000 RPM
TSR
(ft/sec)
Re t
(mi lli on)
1.00
29.99
5 .82
0.2128
0.1586
2.00
42.42
4.11
0 . 2158
0 . 1609
3 . 00
51 . 95
3 .36
0 . 2188
0.1631
4 . 00
59 . 99
2.91
0 .2217
0.1653
5 . 00
67.07
2.60
0.2229
0.1675
6.00
73.47
2.38
0.2237
0.1696
7.00
79.36
2 . 20
0.2245
0.1717
8 . 00
84.84
2 . 06
0 .2254
0.1738
9.00
89.98
1.94
0 . 2264
0.1759
10 .0 0
94 .85
1.84
0.2274
0.1779
Velocities , t ip- speed Reynolds numbers and tip-spe ed
Mach numbers were calcu l ated at the t unn e l temperatur e
of 75 deg r ees Fahrenheit and barometric pressure of
28.81 inch Hg.
A5
r
APPENDIX C
(dl
v
Conti nued
3000 RPM
TSR
(ft / secl
-
**
Ret
(mi ll ion)
1.0 0
29 . 99
8 . 73
0. 3 1 6 6
0. 23 6 0
2 . 00
42.42
6 . 17
0. 318 6
0 . 23 76
3 . 00
51. 95
5 . 04
0 . 3206
0 . 2391
4.00
59.99
4.36
0 . 322 7
0 . 2406
5.00
67.07
3 . 90
0 . 3221
0 .24 21
6 . 00
73 . 47
3 . 56
0. 32 11
0. 2 436
7 . 00
79.36
3 . 30
0 . 3 2 03
0 .24 5 0
8.00
84.84
3.09
0 . 3197
0 . 2465
9.00
89.98
2 . 91
0 .31 91
0 . 2 4 80
1 0 . 00
94.85
2.76
0 . 3187
0 . 2 494
Velociti es , tip-speed Reyno lds numbers and tip-speed
Mach numbers we re calculated at t he tunnel temperature
of 7 5 degrees Fahrenheit and barometr ic pressure of
28.81 in c h Hg .
A6
r
AP PE NDI X C
( e)
v
Co n t inued
4000 RPM
TSR
(m illi on)
(ft/sec)
r
Ret
1.00
29.99
11. 64
0 .4209
0.3138
2.00
42. 4 2
8 .2 3
0 . 4224
0.3 1 50
3 .00
51. 95
6.72
0 . 4240
0.3 1 61
4.00
59 .9 9
5 . 82
0.4255
0.3 1 73
5 .00
67.07
5.20
0.4237
0.3184
6 . 00
73.47
4 . 75
0.4213
0 . 3195
7.00
79.36
4 .4 0
0 . 419 2
0 . 3206
8.00
84 . 84
4 . 11
0.4173
0 . 3218
9 .0 0
89 . 98
3 . 88
0. 41 56
0.3229
10.00
94.85
3 . 68
0.4140
0 . 3240
**
Velo c iti es , tip- speed Reynolds numbers and tip-speed
Mach numbers we re calculated a t the tu nn e l temperature
of 75 degrees Fah r enh e it and ba rometric pr essu re of
28 .81 inch Hg.
r
A7
APPEN DIX C
(f )
v
Co ntinued
5000 RPM
TSR
(million)
(ft /sec)
**
Ret
1.00
29 .99
14.55
0.5254
0".391 8
2.00
42.42
10.29
0 . 5267
0.3927
3.00
51.95
8 .40
0.5279
0 . 3936
4.00
59.99
7.27
0.5291
0.3945
5 . 00
67.07
6 . 51
0.5262
0.3954
6 . 00
73.47
5 . 94
0.5226
0.3963
7.0 0
79.36
5 .5 0
0.5193
0.3972
8.00
84.84
5.14
0.5164
0.3982
9 . 00
89.98
4.85
0 . 5136
0.3991
10 .0 0
94.85
4.60
0.5111
0.4000
Velocities , tip- speed Reynolds numbe r s an d tip- speed
Mach numbers were calculated at the tunne l temperature
of 75 degrees Fahrenheit and barometric pressure of
28.81 inch Hg.
r
A8
APPENDIX C
(g)
v
Concl uded
550 0 RPM
TSR
(million)
(ft/sec)
r
**
Ret
1.00
29 . 99
16 . 00
0 .5777
0.4308
2 .00
42.42
11.31
0.578 9
0.4316
3 . 00
51.9 5
9.24
0.5800
0 . 4324
4 . 00
59 . 99
8.00
0.5811
0.4333
5.00
67.07
7 . 16
0 . 5777
0.4341
6.00
73.47
6 . 53
0.5735
0.4349
7. 00
79.36
6 . 05
0 . 5697
0 . 4358
8 . 00
84.84
5 . 66
0.56 62
0.4366
9 . 00
89.98
5 . 33
0 . 5630
0.4374
10 . 00
9 4.85
5 . 06
0 . 5600
0 . 4382
Ve l ocit i es , tip- speed Rey nolds numbe r s a nd ti p-speed
Mach numbe rs were calculated at the tunnel temperatu r e
of 7 5 degrees Fahrenh e it and barometric pressure of
28 .81 inch Hg.
r
A9
r
APPENDIX D
Plan of Test and Tabulated Data
r
A10
PLAN OF TES T
r
TITL E OF TEST :
Pe r fo rman ce a nd Ae r odynam ic Br aki ng
o f a Hor i zontal - Ax i s Wind Turbin e
from Small- Scale Wi nd Tunn e l Tes ts.
TEST SPONS OR :
Dr . Went z/ Dr . Sn yde r / NASA Le wi s
FACILITY :
Walte r Bee c h 7 x 10 Sub s onic Wind Tunn e l
Wich ita State Univer s ity , Wichita, Kansa s
MODELS:
- NACA 2 30 24 Rot or,
20 in. di ame te r, 1 . 75 in. chord.
-
NACA 2302 4 Roto r,
20 i n . di amete r , 1.75 in. chord,
with 30% c hord a il e ron, 0a = 90 de g. ,
Hinge lin e po s ition! X = O.SOc, Y = O.14c.
- NACA 64 - 62 1 Rot o r,
3
20 in. di ame t e r , 1.75 in. chord.
r
TEST REQUI RED :
Powe r e d Roto r Tes t
TEST LI MITS :
Tunne l q maxi mum 50 psf
r pm maximum
55 00 rpm
DATA OUTP UT:
TEST DATE :
Monday , April 08, 1985
through
Wed nesd ay April 24, 1985
WR I TT EN BY:
Hoa V. Cao
DATE:
March 11 , 1 98 5
r
All
TEST SCHEDULE
r
Run i
RPM
NACA 23024
20 in. Rotor
30% chord aileron , 6 = 90 deg.
Hinge lin e Position : a X=O .80c, Y=O . 14c
Gap Fully Open .
1000. 2000 .
3000 . 3500.
Same as Run #3
F. W.
Same as Run #3,
Gap Full y Closed
600 , 1 000,
2000 . 3000 .
3500 .
14-20
NACA 23024 Rotor without Aileron
1000 . 2000 .
3000 . 40 00 .
5000 . 5500 .
780.
21-27
NACA 64 -6 21 Rotor
3
720 , 1000,
2000. 3000.
4000. 5500 .
28
NACA 64 -621 Rotor
3
F. W.
29
NACA 23024 Rotor , wind Milling
F. W.
31
NACA 23024 Rotor with D.3 0c Aileron
Blade Locked to Ro t o r Ba l ance
o
3- 7
8
9 -13
r
CONFIGURATION
Gap Fully Closed
o
Same as Run # 31
32
Gap Fully Open
33
Same as Run i3 , Gap Ful ly Clo sed
F . W.
34
NACA 64 -621 Rotor
3
720
NACA 6 4 - 621 Ro tor
3
2000
NACA 23024 Rotor
4000
NACA 23024 Rotor
wit h 1 , 2 and 3 Transition Strips
3000
NACA 64 - 621 Rotor
3000
35 . 36
37
38-40
41-43
Wit h 1, 3 2 and 3 Transit ion Strips
r
••
Free - Wheeling
A12
••
I~ur ,
n UMb e r
:5
APRIL 12/
1985
WENTZ - SNYDER - NAS A LE WIS
NACA 23 02 4 POWERED ROTOR WITH BALANCE
PRO P . DIAM,
VW
(FPS)
VT/VW
29,7 4
42,01
51,42
59, 41
66 .41
2 .93
2 ,0 8
1.7
1. 47
1 ,31
T
Q
(~ t )
= 1,667
CQ
CP
(t' t-lb)
P
(WA TTS)
CT
(lb )
Q
(P SF )
1 .16 0 0
1, 6040
2,0020
2.376 0
2 ,690 0
- 0.1705
- 0,1 650
-0 .1 565
-0, 1535
-0.15 20
-24 ,21
-23, 4 3
- 22,22
- 2 1.79
-21.58
'0,53774
0, 37279
0,31050
0 ,2 7654
0.25057
- 0 , 04741
- 0 , 0 2 300
-0,0 145 6
- 0.01 072
- 0.00849
- 0,13914
·~ O, 04780
-0 ,02472
-- 0,01 574
- 0,01116
0.99
1 ,97
2 . 95
3 . 94
4, 9 2
REYN OLD S NU MB ERIFO OT ::: 545408.
MACH NUM BER= . 05 87
RPM = 10 0 0
(RE AND MAC H NO. CALCULA TED FROM LA ST POINT)
Run n UMb er 4
APRI 12/ 1 985
SNYDER
NASA LEWI S
NACA 2302 4 PO WERED ROTOR WITH BALANCE
WENTZ
-
-
PROP. DIAM,
r
VW
(FPS)
VT/ VW
6S . 7S
72.2
78 .07
84 . 06
89 .1S
93. S8
98 ,64
1 03 . 02
1 07.3 2
:\.10.97
:\.1 4,8 9
:\.18.79
122 .46
1.26. 1 5
130 . 3
133 . 3 3
1. 33
1. 2 1
1. 12
1. 04
. 98
.93
. 88
. 8S
.8 1
. 79
.76
.73
, 71
. 69
.67
,65
T
Q
(ft> = 1.667
<lb)
(t' t - lb )
P
(WATTS )
2 . 6720
2,98 40
3,2780
3,5620
3 , 8 060
4.0400
4.2700
4.49 40
4.7100
4,89 2 0
5, 1 220
5,3180
5 .568 0
5 .7680
6,0 260
6,2100
-0, 1 5 00
-0 .1 500
- 0,1510
-0 , 155 0
-0 , 1620
- 0,1690
-0,1750
-0, 1 8 1 0
- 0.1 885
-0 .1 90 0
-0,1980
- 0,2065
- 0.2165
- 0,2 28 0
- 0, 2 430
- 0,2530
- 21. 30
-21.30
-2 1. 44
-22 ,01
- 23 . 00
-23, 9 9
- 2 4.8 5
- 25 , 70
- 26 .76
-26.98
- 28 . 11
- 29,32
- 3 0 , 74
-3 2 , 37
-3 4, 50
-35 , 92
CT
0.25396
0. 23561
0, 22 137
0 . 2 075 2
0, 1971 3
0.1 9025
0 , 1810 0
0.17464
0.16897
0,16414
0, 16034
0.15601
0 . 15369
0,15032
0, 14 719
0,1 44 86
CQ
CP
Q
(P SF )
- 0,0085 5
- 0 , 00710
- 0 ,0061 2
- 0,0054 2
- 0,00503
- 0 ,0 0 47 7
- 0.0044S
- 0.00 42 2
-0,0 0406
- 0 .0 0382
- 0,00372
- 0.00363
- 0,00358
- 0.00356
- 0.0 03 56
- 0.00354
- 0,01135
- 0.0085 9
- 0,00684
-0.00 56 2
- 0.00493
-0.0044 5
- 0.003 9 4
- 0,003 5 7
- 0,00330
- 0,00301
- 0 . 002 82
-0.00267
- 0,00256
-0,00247
- 0,00239
- 0.0023 2
4 ,82
5.80
6 ,78
7,86
8,85
9,73
10.81
11 .79
12, 7 7
13, 6 6
14.64
15,62
16. 6 0
17,58
18. 7 6
19,6 4
REYNOLDS NUMB ER/FOO T", 974495.
MA CH NUMB ER= .11 73
RPM = 1000
(RE AND MACH NO. CALCULATED FROM LAST POINT)
A13
,.
1<uri nUMber 5
12, 1 1, IJ5
NA S A L.EWIS
NACI': 23 02 4 POW[ nED ROTOt~ WIT H BALANCE
Af'I< lL
WENTZ - :;, N (J)L1~
PROP,
VW
(FPS )
VT/V W
29 .92
4 1 .15
5 .83
51,71
3 . 38
58 . 9 1
67 .3 2
73
2 , 96
78,9
8 4.33
89 .93
'1 4.26
4,24
2.59
2.39
2.2 1
2 .07
1. 94
1. 85
DIAM.
-
(f t )
Q
r
(lb )
(ft - lb)
(WATT S)
2.0360
3.1800
4.1 9 60
4.6200
5 . 2 400
5,6580
-0 .70 85
- 0.6940
- 0.6490
- 0 . 6630
6,1000
-0.6505
-201. 18
- 1 97.06
- 184.28
- 191 . 24
- 19 0.95
- 188. 26
- 184. 71
6 . 5760
-0 . 651 0
-184.85
7.0400
- 0,6530
- 0.6460
- 185 . 42
- 183. 4 3
T
7 .3740
- {),673S
-0.6725
= :1.. 667
cr
C(~
cr
- 0.195 7 4
- 1.14186
0. 99
- 0.10119
1. 89
Q
(P S F)
0.93766
0.77289
0.64722
-0. 06 00 5
-0.4 2921
- 0.20274
0 ,54905
-0 . 04801
- 0,14 229
3,8 6
0.47677
0 . 43786
0.4048 5
0.3820 2
0.35967
0,34293
- 0,03671
-0 .03078
- 0.09 51 8
5.04
5 . 92
6.90
- 0,0 259 0
- 0 . 02269
- 0. 02001
- 0.01802
2.97
- 0 . 07360
- 0 .0 5730
- 0.04696
7,89
- 0,03885
- 0,03338
8.97
9,85
REYNOLD S NUMBER /F OOT= 7 3 6171.
MACH NUMBER ~ . 0 8 31
RPM :: 2 0 00
(R C ~ ND MACH NO. CALCU LATED FROH LAST POINT)
R uti nU Mbe r
b
APRIL 1 2, 1985
WENTZ - SNYDER
NA S A LEWIS
NACA 23024 POWE RED ROTOR WITH BALANCE
-
PROP . DIAM.
OW
VT /VW
(F PS)
2fJ .98
42, :~
S 1. 84
59.82
66,86
8,74
(:,. 19
5. 05
4.38
3.92
r
(ft>
<It! )
Q
(ft - lb)
p
(WATTS)
2.504 0
3,7760
5,4340
6 .5560
7.7860
- 1. 8265
- 1. 67 45
-1 ,638 0
-1.6365
- 1.54 80
-777.94
- 713.20
-697.66
-6 97.0 2
-659 . 33
= 1. 667
cr
1, 14 9 17
0 .870 47
0.83560
0.757 0 7
0.7 1973
CQ
CP
- 0. 5 0 285
-0 . 2 3 1 56
-0 .1 5110
- 0 .11 337
-0.08584
- 4.39 2 44
-- 1.4 3359
- 0,76328
- 0 . 4 9627
-0.33 621
REY NOL.DS NUMBER /FO OT= 543500,
MA CH NUM BE R= . 0589
RPM = 3UllO
(RE AND MACH NO, CALCULATED FROM LA S T P OI NT>
A1 4
Q
( P S F)
1. 00
l ,99
2. 98
3.97
4 .96
r
AP RIL 12,
t~i"ns
WENTZ - SN YDER - NASA LEWI S
Nt~CA 2 3 02 4 P O W E '~ ED rW T OR WIT H fCA L ANCE
PRO P.
VW
(FPS )
VT /VW
30 .0 3
l O .l ?
4 2 ,4
7. 2 1
5.89
5 1. 8 8
59 .1 5
66.9 4
5 ,16
4.56
DIAM.
Cf t) = 1.667
cr
CT
CQ
- 1225 .87
- 1 20:\. .0 3
1.15547
0. 93721
-0.679 11
- b.90754
1. 0 0
-2.40567
-2.2355
- 1110, 9 4
0.8368 1
1. 99
2 . 98
- 2 ,0 675
- 10 27 . 36
-- 10 93.20
0 , 8248 4
-0.33387
- 0. 2062 1
- 0.14 673
-0, 12190
(I
P
(l b )
( ft - lb)
( WATT S )
2,5180
4 .0 '700
- 2.467 0
S.4420
6 . 972 0
8 . 3 02 0
T
--2 .41 70
-2 .2000
0.76683
Q
(P SF)
- 1. 214 16
- 0. 7578 1
- 0,55629
3 .87
4. 9 6
REYNOLDS NUMBER / FOUT = 5 42 4 33 .
MACH NUMBER = . OSB9
RPM=
3S fI 0
(R E AND MACH NO. CALCULATED FR OM l.AST P OI NT>
_ ._ R"n
n UMb e l '
S
APR I L 18, 1985
NA S A LEWI S
WENT Z - SNYD ER
NAC" ;~3 0 2 4 POWERED RO TOR WITH BALAN CE
-
PROP, DIAM. Cft )
VW
RPM
T
VT /VW
(FPS)
29.78
42. 11
5 1. 58
58.H l
66. S 9
7 3.02
7B.87
83. '7 8
8 9. !i'2
94 . 27
(LEt>
- j.80
-2 70
- 330
-39 0
-450
-48 0
-540
-5 70
-·60 0
- 636
- . 53
- . 56
-.56
- . 58
- . 59
1 .282
- .57
1. SS 4
- .6
1.824
2. 0 74
2.4U2
2 . 638
- . S9
- . 58
- . 59
.24
. 482
.74
I
1. 667
CT
Q
CQ
CP
. 11 2 03
.11 25
.11514
. 11 967
.11967
.12 088
. 12 161
. 1 2253
. 12 319
.1 23 12
0
-. 00 5
- .0035
- .004
- .00 2
-, OOS
- .O OS
- .OIlS
- , OO S
- .005
NU HI)Er~
NUHE!ER=
0
- .0007
-. 0003 3
- .QOIl29
- . 00 011
- ,00 0 23
- . 00 02
-.000 19
- .00015
- , 00014
IFO() T = 731592.
,OB2 9
r
A15
Q
(PSF)
(FT-LEt)
RE YNO LDS
MACH
~
0
. 000;';1;9
. 00018
.00017
.00007
.00 01 3
. 00012
.OO O:ll
.00009
.aOO09
. 98
:l.96
2. r}4
3 . 83
4. (.iii
5.8 9
6,8 7
7.7 6
8. 93
9.82
l~
u r,
nutlber'
9
-
WE.N TZ
f'U~,CA
APRIl
12,
SNY J) E I~
VW
VT/VW
2 9 .46
41. 62
5 0 . en;,
58 .89
65.17
7 1.51
77 . 88
8 3 .25
88.87
93 .63
9 7.8
1. 70
1. 26
1. 03
. 89
.8
, 73
. 67
.63
.59
.56
. 54
j985
NA SA LEWIS
2302 4 POWE RED ROHm WITH BALANCE
PRO P . DI AM.
(FPS )
-
(f1')
1
Q
P
( Ib )
(f t- lb)
(WATT S )
0 .7820
1. 11 B 0
1 ,3 8 60
1.6640
1.9900
2 , 2360
2.4400
2.7160
3.0000
3.3080
3.4840
-0 .0 2 4 5
- 0.026 0
-0,0345
- 0.0360
- 0,()4 25
- 0.0425
- 0.0450
- 0.0450
-0.O51()
- 0.0520
- 0,nS20
-2 ,0 9
-2 . 2 1
-2.94
- 3.07
-3.6 2
-3.62
-3 . 83
-3.83
-4,34
-4.43
-4.4 3
= :I. • 66"
C1
0.36354
0. 26 031
0,21530
(1. 1 9393
0 .18934
0.17672
0.1 6258
0.15836
0,15378
0.1 52 78
0. 14 776
CP
CQ
- 0.00683
- 0. ()036 3
- 0.00321
-0,0025 2
- 0.0 0243
- Q, 01l201
- 0.00180
- 0.001 57
-0.00 1 57
- 0.00144
-,0.0 0132
Q
(P SF)
- 0.01215 0.99
- 0.00457 1,97
- 0.00330 2.95
-0.00224 :.1).93
-' 0 .00 195 4,82
-0.00148 5.80
'-0.00121 6.88
- 0. 00099 '7 ,86
- 0.00092 8.9 4
- 0.00081 9.92
- 0.00071 10.80
REYNOLDS NUMBER/FOOT= 78 2 981.
MACH NUMBER = .0 869
RPM =: 600
(R E AND MACH NO. CA LCU LATED FROM LAST POI NT>
R ur, nUMber
10
APRIL 12, 1985
SN YDER
NA SA LEWI S
NA CA 23024 POW ERED RO TOR WITH BALANCE
WENT Z
-
-
PROP. DIAM. ef' t ) = 1. 667
VW
(FP S )
VT/ VW
29 .S7
4 1 .77
51.12
59.06
65 .29
2.95
2 . 09
1. 7 1
1. 48
1, 3 4
Q
P
Db)
(ft- l b)
(WATTS)
1. 3500
-0. 1175
- 0.0 9 30
-0.0700
- 0.06 65
-0.0690
-16.68
-13.20
-9.94
-9 .44
-9.80
T
1.9980
2. 4360
2 .7860
3.132 0
CT
0,62493
0 , 46367
0.37741
0.3 2 400
0.29747
CQ
CP
- 0.03263
·- 0.0129 5
- 0.0065 1
- 0,00464
-0 .00393
- 0.09630
-0.02705
- 0.01111
- 0.00686
- 0.00526
REYNOLDS NUM[lER/FOOT= 549966.
MACH NUMBER = .0581
RPM = 1000
(RE AND MACH NO. CALCULATED FROM LAST POINT)
A16
0
(P SF)
11.99
1. .97
2.96
3.94
4,82
r{ U Il
n UMbi!I' 11
AP RIL 12, 1 985
WENT Z - SNYDER - NASA L EW IS
NAC A ? 3024 POWER ED ROTOR WITH BALANCE
PROP.
OW
( FP S >
VT/VW
29 .68
41. 94
50, 4 7
5 9, ';:~2
6 6,18
5 .88
4 .16
3, 46
2.95
:~. 64
T
DI AM.
(ft)
Q
= 1. 667
P
Ob)
(f' t-lb )
( WATT S )
2.0720
3,67 40
4. 8780
'5 . 6420
6. 4400
-0 . 6685
- 0.5515
-0,4955
- 0,51 25
- 0 . 4 965
-
CT
189,82
156.60
140,70
145.S2
140,98
0.95399
0.8472 7
0.7767 2
0,6526 4
0 . 59651
CQ
CP
- 0 . 1846 4
-0.07629
-0.0 4733
- 0.03556
- 0.02759
- 1.08586
- 0 .3175'5
- 0.16369
- 0.1048 3
- 0,0727 7
Q
(PSF )
1. 00
t.99
2,88
3 .96
4.95
REYNO LDS NUM BER /F OOT = 554943,
MACH NU MB ER = .0 588
RPM:: 2000
( RE AND MACH NO , CALCULATED FROM LAST PO INT>
Run n UMber 12
APRIL 121
19 65
WENTZ - SNY DER - NAS A LEWI S
NACA 2 3 02 4 POWERED ROTOR WITH BALANC E
PROP. Dr AM.
OW
(FP S )
VT /VW
29,68
40.89
5 1, 46
59.38
66 , 37
8.8 2
6.4
5.09
4.41
3 , 95
T
( ft )
Q
P
<lb)
(f' t -lb)
( WATT S)
2 ,0 7 00
3.65 0 0
6 . 2 06 0
7,6040
9 ,0 48tl
- 1.8355
- 1. 699(J
- 1,352 0
'- 1. 2735
- 1 . 1585
- 781.78
-723 , 64
- 57 5 .8S
- 542.41
- 493. 4 3
::
1.667
CT
CQ
CP
0 .95308
o . 88549
0,9524 7
11.876 37
0, 8 3481
- 0.50696
-11.2 472 6
- 0,12 4 48
- 0,08 8 05
- 0,06412
- 4. 4 7226
-1. SB3 29
- 0. 6333 8
'- 0. 38823
- 0 ,2529 7
REYNO LD S NUHB ER/FOO T= 55 46 22.
MACH NUMB ER= . 0589
RPM:: 3000
( RE AND MACH NO . CALCULATED F RO M LAST POINT>
r
A17
Q
(PSF )
1. 00
1.89
2, 99
~3. 98
4.97
APR I L 12 } 1 9B'.:i
WENT L -
r
SNYDE R -
NACA 23 02 4 POWE RE D
PROP.
VW
VT/ VW
(FP S )
DIAN.
NA S A l.e WIS
nOTO~
(ft)
Db)
(f't-lb)
p
( WATT S)
T
Q
29.69
41. 99
10 .29
1 ,8820
-2.5295
- 1256 . 93
7 . 27
- 2. 4 535
5Q,S5
58 .61
b.04
5,21
3.B400
5.29 20
-2 , 2 63 0
- 121 9 . 1 6
- 11 24.5 0
66,4 1
4 .6
-2. 0 3 95
- 1 . '1 440
- 1 013 . 44
-86 6 .61
b,BBBO
9,7 5 60
UIT H 8ALANC E
= 1 .667
CT
CP
CQ
Q
<PSF)
0,06774
1l . 8 BS Ol
- 0.6 9963
- 0. :-S39 21
- 7.19877
0 ,8 4 174
0.81503
0,89918
- 0 ,2 1 593
- 0.1447 7
- 0 . 0964 ;~
- 1.30 4 94
- 2 . 46763
- 0,75 4 60
- 0.443 5 9
11 , 99
1, 9 17
2.88
3 , 87
4 ,97
RE YNO LDS NUMBER/FOOT:::: SS 4BfJ8 .
MACH NUMBER ::::
.OS '7
RPM= 3500
(R E AND MACH NO.
Run nUMb e. r 14
CALCU LAT E D FROM LA ST P OINT>
AP RIL 12, 1985
SNYDEI~ - NA S A LE WI S
NAC A 2 3 02 4 POWERED RO TOR WIT H BAL ANCE
WEN TZ -.
PROP, DIAH,
vw
VT/VW
(FPS>
29 .6
41.8 5
5 1. 2 3
S9.1 4
65, 45
72,4.1
71'1. 2 1
83.6
88.6 6
92.99
97.S7
102.89
106.23
110.66
1 1 4.5 4
118 . {) 4
1 2 1 .69
125 . 58
12 9. 36
132 . 5
2 . 95
2 ,09
1 .7
1. 4B
1. 33
1. 2 1
1 , 12
1. 04
.98
.94
.89
.85
,82
.79
,76
.7'
,72
.7
,67
. 66
T
(ft)
~
1,667
CT
Q
P
Clb )
Cft-lb)
(WATT S)
1,0 660
1,4960
1 ,87 40
2.216 0
2 ,5740
2 ,9000
3,1740
3 , 45 20
3,6800
3 , 9 120
4 ,1 880
4,4660
4,6960
4,9520
5, 03 60
5,3080
5, 5 420
5,7980
6 ,0640
6 ,2560
-0 , 0 150
-0 , 0100
-0 ,0045
0,00 5 0
0,008 5
0 ,0115
0,0150
0 , 0200
0,0240
0 ,0270
0, 03 0 0
0. 0 35 0
0, 0350
0,0400
0,0 4 50
0 , 0 4 70
0 ,0 500
0 . 0550
0 , 0600
0 . 0640
- 2 , 13
- 1,42
-0 , 64
0,7 1
1. 2 1
1. 63
2, 13
2 , 84
3 ,41
3. 83
4, 26
4,97
4 ,97
S . b8
6 , 39
6.67
7, 1 0
7 ,81
8 , 52
9,09
0 , 494 5 2
(j,34783
0,2907 4
0 , 25799
0,244 6 8
0,2 2S2 0
0 , 21132
0,20113
0, 19 062
0, 18424
0, 179 1 6
0, 172 12
0 , 16977
0 .1 6 4 97
0, 15660
0, 15572
0, 15297
0, 15 0 27
0, 148 11
0 .145 9 3
CP
CQ
- 0 . 004 17
- 0,001 39
-0,00042
Q, {)003S
0,000411
0,1)0054
0,00060
()'00070
0,00075
0,000 7 6
0,00077
0,0 0 08 1
0,00076
- 0, 0123 1
- 0,002 9 1
- 0,00 071
O , OOO S O
0,0008 4
0 , 00083
0.00083
0,00086
0 ,000 8 8
0, 0 0090
RE YNOLDS N U M B E R / FOO T ~ 989 626,
MA CH NUMBE R= , 11 72
RPM ::. 100 0
(R E AND MACH NO, CALC ULAT ED FRO H LAS T P OINT)
A1 8
Q
<PSF)
O,OO OS Z
0,00 065
a,0 0 06S
0,00 067
0,00013
0,00 0 7 3
0,00 072
0,0 00 69
0, 000 69
0,000 62
0, 000 6 3
0 , 0 0 06 4
0, 00 06 1
0, 0005 9
0 , 00 059
0. 000 59
0, 0 0 059
0. 99
:1. ,97
2,95
~~, 9 4
4,82
5,90
b , OB
7,0 6
8.85
9,73
1 0,7 1
11 ,8 9
1 2.67
13 ,75
14 .73
1 5 .6 2
16 ,6 0
17 .68
1 8,7 6
19 , 64
Rur. nUM be r' 15
AP!{ It.
WENTZ -
1~~ /
i'illS
- Ntlt)A LEW IS
NACA 2J02 4 POWE I{£D rW f(JR WITH [tALANCE
S NYD£r~
PROP. DIAM. (f t ) = 1.667
VW
(FP S )
VT/VW
29.77
42 . 0 1
5 1 . 41
59.32
66,3
72.6
77.84
83.8
88.86
93 . 19
5.86
4.1 6
3.4
2 .94
2.63
2.4
2.24
2.08
1.96
1. 87
1. 7 8
1.69
1. 63
1. 58
1. 5 1
'n .86
103.52
1 07. 26
1 1 0.48
115. S3
T
Q
P
(lb )
(ft-lb)
(WATTS)
2.12 0 0
3.0480
3.8900
4.4680
5. t14tJ
5.5440
5.9 060
6.42211
6.8300
7.148 0
7 . 558 0
7.9940
£),3 8 00
8 ,67130
9.1680
0.0615
-().02 2 5
-0.03110
- (). 0400
- 0.()40 0
- n.O S1S
-0 . ()485
- 0.0440
-0.0 385
-0 . 032 0
-0.0265
-0.0200
-0.01 6 0
-O,012()
0. O03()
17.46
-6 .39
-8. 52
- 11 .36
- 11.3 6
-14 . 62
- 1 3 . 77
- 1 2.49
-10.9 3
-9,09
-7.5 2
-S . 68
-4.54
-3 .41
0.135
CQ
CT
CP
Il
( P SF>
o .97573
0.7 0456
11.60048
0.51798
0,47463
0 . 429 10
0.3 97 7 0
0.3 7 3 13
0. 3 5286
0.3 3 58 1
0.32257
0. 3 04 9 1
0 . 29771
0.29 058
0.2807 8
0.01698
- 0.0031 2
- 0 .0 0278
- 0 .00 2 78
- 0 . 002 23
- 0 .00239
- 0.0 01 96
-0.00 1 53
-0 . 0011 9
-0.0 00 90
-0. 00068
-0.00046
-0,0 0 034
- 0.0 0024
0.00006
0.09956
·-0. il1296
- 0,00943
- 0. 00819
- 0.00586
-0 . 00575
- 0.00 4 39
-0,0 03 1 9
- 0.00234
- 0.00 169
-0, 00121
-0.00 077
- 0 . 00055
- 0 . 0 0038
0.000 08
1. 00
t .98
2.'"17
. 95
4. 9 4
5,92
6.80
7.89
8.87
9.75
10.74
12.0 1
12.90
13.68
14.96
~.~
REY NOLDS NUMI~E R/FOO T = 8888 5 9 .
MA CH NUMBER= . 1023
RPM ::. 2000
IRE AND MACH NO . CALCULAT ED FROM LAST PO IN T>
Ru n
nU Mb er'
16
APRIL 12/ 1 985
WEN TZ - SNYDEI{ - NASA LE WIS
NA CA 2 3024 POWERED ROTOI~ WIT H BALANCE
PROP. DIAM.
VW
( FPS)
VT / VW
29.84
42 .19
S 1 ,64
59,5 4
66.53
72 . 95
78. 6 6
84.06
89.1 4
93.94
8.78
6.21
5,07
4.4
3.94
3.59
3.33
3. 11
2.94
2.79
T
Q
(lb )
(ft -lb)
2.4640
4. 3 2;.~0
5 .9040
6.3900
7.1740
8.0120
a.bl 0 11
IJ.2460
9.8260
10.324 0
-0 . 0295
0.1 27 0
0.32 50
O.10Sf)
-0.0010
·-().00'70
-0.03 05
- 0.0090
-0 .027 U
-0.0450
(R E
(ft)
P
(WATTS)
-1 2.56
54.0?
131L 4;?
44.72
-0 . 43
- 3 . 83
-16 . 40
-3.83
-11 .50
-19.17
= 1.667
CT
CQ
CP
1 . 13 1 15
0,99 43 0
0, 9 068 1
IJ.738 13
0. 66 3 7 7
0 .6 1821
0.57 04 2
0 . 5 3 S79
O. SOb 3 8
0 . 47 90 5
-0 . 008 12
0.01753
0.0 299 4
0.00728
- 0. 0000 6
-0.0 00 4 2
-0 . 00 153
- 0 . 0 00 3 1
- 0 .00 003
- 0 .0 01 25
-0. 07 129
0.1 0878
0.15 185
0 .03200
-0,00022
-0 . 00 1 50
-0, 00 509
-0.00097
-0, 00245
- 0 .0 034 9
REYNOLDS NUMBER/FOO T: 7 44 465 .
MACH NU MflER = . 083 1
RPM:: 3000
AND MAC H NO. CALCULATED FROM LAS T POI NT )
A19
Il
(P ::W)
1. 00
1. 99
2 .98
3.97
4 ,95
15.94
6 .92
7.'li
8 . 09
'7 . 87
Ru rl nUMbe r
17
AP I~IL
12, 1965
WENTZ - SNYDER - NASA LEWI S
NACA 2302 Q POWERED ROTO R WIT H BALANCE
PROP, DI AM,
VW
(F PS)
VT/VW
T
29 ,99
4 3 . 27
5 1 .69
5 9, 72
67 . 3 9
11,68 2.69QO
8,07
4, 97 00
6,75
6.72211
5,85
8 . S 000
5 ,1 8 10,0 22 0
<lb)
(f t )
Q
(ft- lb )
P
(WATT S)
-0, 11 50
- 0.0135
0, 1265
0,3 125
0, 5650
-65,3 1
-7 ,67
71. 84
177,4 7
3 20.8 6
= j . ,66 7
CT
1.23462
1,08726
1. 03 034
0, 97800
0,90 5 4 9
CQ
CP
- 0,0 3 162
- 0,00177
(),01163
0.021 57
0 ,03062
- 0 . 36925
- 0, 0 1430
0 . U7857
0,12611
0,15866
Q
(P SF)
1. 00
2,09
2 , 99
3 .98
5,07
RE YNOL DS NUMBER/F OOT= 553 40 2.
MACH NUMBER = ,0 596
RPM = 40 00
( RE AN D MA CH NO. CA LCU LATED FROM LAST POINT)
Rurl nUM ber 18
APR I L 12 , 1 985
SNYDER - NA SA LE WI S
NA CA 23024 PO WER ED ROTOR WIT H BALANCE
WENTZ -
PROP, DIAM, (f t) :: 1.667
VW
( FPS)
VT / VW
29 . 9S
42.3
S O . 17 2
59. 76
66 . 13
1 4 .57
10 ,32
0,57
7,3
T
Db )
b,b
2,9340
5 . 2620
7 . 3 4 80
9, 3 580
11.11 80
Q
(f t - lb )
P
( WATT S)
-0 . 2 0 0 0
- 0.1500
- 0,0 54 0
0,08 35
0.2355
'-1 41, 9 7
- 106.48
-3 8, 3 3
59,27
167,17
CT
1.34 2 20
1 .Z0631
1,16259
1 ,07500
1 , 0431 4
CQ
CP
-- 0,05488
- 0 .02063
- 0 ,00 513
(J,0 0S 7S
0,01325
-0.79982
- 0 . 21280
- 0,04 39 2
0 . 04202
0, 087 48
REYNOL DS NU MBER/ FOO Tz 544040,
MACH NUMBER = , 05 84
RP M:: SO 0 0
( RE AN D MA CH NO, CALC ULA TED FROM LA ST POINT)
A20
Q
(PSF)
1. 00
, 00
2. 9 0
3. 99
4 .88
;.:~
r
API< l L 1"
L
HUll nU Mhel' ,9
1 985
NA !JA LEWIS
POWERE D NO TOR WI TH BALANC E
WUHl - SN yn E.R
NACA
2~ 02'1
PROP. DIAM.
VW
VT /VW
2 9.96
42 .3 1
5 1. 8
59 . 7 Cl
67 .47
T
<1 b )
<FPS)
16.02 3.0500
11.35 5 . 3260
7.7120
9 . 27
8.03
9 . 8220
7.12 11 .6980
,
-
(f
t)
Q
P
<ft -l b)
(WA TTS)
- 0.2 4 7 0
- 0. 2 0 9 0
-0 ,1 235
0.0005
0.1465
- 192 .87
-163. 2 0
-96 . 44
0 ,39
114.40
= 1. 667
CQ
CT
CP
Q
(P SF)
1.3940 6
1 .22 069
"1791 8
:t,1 2 732
1.054 32
- 0.06772
- 0.1l 2B74
- 0.01133
0.110003
0.00792
- 1.0 85 14
- 0. 326 04
-0. 1 0498
II.B00 28
0.05636
.. 0 0
2.0 0
3. 00
3.99
S. 08
REYNOLDS NUMBER / FOOT= 554016.
MACH NUM BER= .0 596
RP M= 5 500
(RE ~ND MACH NO. CAL CULATED FROM LAS T PO INT)
Rurc nUM ber 20
r
APRIL 12, 1985
WENTZ - SN YDER - NAS A LEWIS
NACA 230 2 4 POWE RED ROTOR WITH BALANCE
PROP. DI AM.
VW
VT / VW
( FP S)
93 , '7
103.1 6
11 1 ,3 5
118.35
1 26 . 2 7
132 .86
139 . 65
145.36
1 5 1 .6 1
157.76
1 63.2 8
17 6 .39
1 BB, 7 4
2 00.6
2 12. 0 3
T
<lb)
.73
, 66
,61
,58
.S4
, 5 .1
,49
,47
.45
,43
.42
,39
, 36
,34
.32
3. 3 86 0
3,8 400
4, 28 40
4.7040
5 .2100
S.670()
6,1 3'10
6.5540
7 , 0 440
7.50 4 0
7,9560
9 . 1460
10. 2520
11 .3540
12.5280
<f t ) = 1.667
Q
P
(ft - lb )
(WA TTS )
0.0300
0. 0360
0,0455
0.054 5
0.0640
0.07 35
0.0820
0.0915
0.1005
0.1125
0 . 1200
0.14BO
0.1760
0.20 55
0 .2 3 60
3,32
3 . 9(7
5.04
6 .04
7 . 09
8. 14
9.08
111 . 13
1 1.13
12.46
13.29
1 6.3 17
19.49
2 2 ,76
26 .1 3
CT
CQ
Q
<P S F)
0 . 15794
0.1480 5
0.14 176
0,13804
0 . 13 4 3 1
0. 13229
0.1 2 95 2
0.1 2797
0.1264 3
0.124 63
0. 12336
0.12 196
0.1196 2
0.1175 0
0.11648
0.00084
O.1l0083
0.00 090
0.00096
0. 000 99
0.00103
0 .00104
0.0010 7
0.00108
0.0011 2
0.00 11 2
0.00118
0. 00 1 23
0.00 12B
0 . 001 32
REYN OLDS NUMB ER/F OOT ", 1 .3 3 719 E+0 6
MACH NUMBER= .1857
RPM = 7 BO
( RE AND MACH NO, CALCULATED FROM LAST POINT )
A21
CP
0 , 00061
9 . 82
O.IlOO SS 11.88
0. 0005 5
0.000 55
0 . 000 5 3
0.00053
0.00051
0.11005 0
0.00049
0 . 000 48
0.00047
0.0004 6
0. 0 00 44
0. 0 0043
0.00042
1 3.B5
1 5. o s.
17. 7 7
19 .6 4
2 1 .70
2 ~:L 47
25.5 3
27.59
2 9. 55
3 4 .36
39 .27
44 .27
49 .28
WEN
rz -
APki L 1;!,
S NYDE r~
-
ROTOI~
NACA b4-62 1 POWERED
PROP. DIAM,
VW
VT/VW
(FPS )
2 9.83
4 2, 1S
5 1 .6
60, :H
66 .65
73.0 1
78.78
T
(ft)
Q
P
(f'T - lb )
(W ATTS)
1,2460
0,0100
0,0100
1. 5820
0,014 5
1. 0 2
1. 02
1. 48
1. .74
2. 04
2 . 56
2 .66
<lb)
2. 11
1. 49
1. 22
1. 04
.94
.06
.8
1905
NflSA l.E WI S
0,8 4 20
1,91 2 0
0. 01 7 0
2.216 0
2 .4560
2 . 726 0
0,02 00
0, 0 250
0 .02 6 0
WITH BALANCE
= 1 . 667
CT
0.39126
0.28997
0 . 24562
0.2173 1
0 . 20656
0.19083
0.18158
CQ
0.00279
0,00140
0,00 1 35
0,00 11 6
0,00112
0,00 11 7
0 . 0010 4
CP
0,00S87
0.002 08
0.00164
0 ,0 01 21
0.0010 5
0 .00 1 0 0
0. 0 0083
Q
<P SF )
0.99
1. 97
2.95
4.03
4 .92
S.9 0
6.88
REYNOLD S NU MBER/FOO T= 628362.
MACH NUMBER= .0 69 4
RP M= 720
(RE AND MA CH NO. CALCULATED FROM LAST POI NT )
Rur, n UMb e r 22
-
WEN TZ
NACA
APRIL 12, 1 9 85
SNYDER
PROP . DIAM,
VW
VT/VW
(FPS )
2 9.89
42.19
5 1 .68
59.66
66.69
73 .04
79.45
T
(lb)
2 . 92
2. 07
1. 69
1. 46
1. 31
1.19
1.1
1 .18 40
1. 772 0
2. 1700
2.5 660
2.9 040
3.282 0
3.5940
-
NAS A L E WI S
64-621 POW ERE D ROTOR WITH BAL ANCE
(ft)
Q
P
(ft - lb )
(WATTS)
0 . 0250
0.0220
0 .0200
0.0250
0.0290
0.0300
0.0315
3. 55
3.12
2 . 84
3.55
".1 2
4.26
4.4 7
= 1.667
CT
CQ
Q
(PSF)
0 . 54877
0.4 11 57
0.33642
0.29854
0.27 042
0.25474
0.2358 1
0, 00695
0 . 00307
0.00186
0 ,0 0174
0 . 00 1 62
0.001 4 0
0. 001 24
REYNOLDS NUMBER/FOO T= 631091.
MACH NUMBER = .0699
RPM= 1000
(RE AND MA CH NO. CALCU LATED FROM LAS T POINT)
A22
CP
0 . 02030
0.00634
0 .0 03 14
0.00255
0 . 0021 2
0 .00167
0. 001 36
0.99
1.97
2 . 96
3.94
4.92
5 .90
6.98
r
I~ UI'
APR IL 12, 1985
n utlber 23
WENTZ - SNYDER - NASA LE WI S
NACA
POWERED ROTOR WITH BALAN CE
6~ - 621
PROP,
VW
VT/VW
67,5 3
73.22
79,63
(ft)
= 1.667
CQ
P
( WATT S )
0.0665
0 .145 0
0.1250
18.88
1.07161
0,01833
0,10660
41.17
0.75981
0 . 6 0935
0.02009
0,011 57
0 .08281
2,92
2.59
2 , 38
2.3320
3 , 2900
3.9480
4.5 86 0
5.1740
0.00556
0.00409
0 . 4360 2
0.00432
2, 1 9
6.1290
0.0750
0.0930
0.100S
(),S3154
0.4708 1
0. 4 0100
0 . 00395
5.81
4.12
3,37
5 . 6340
CT
CP
Q
(f't-lb )
T
<lb )
(FPS)
30 . 02
4 2.35
5 1. 85
5 9.83
DIAM.
3 5 .4 9
22 . 72
0 . 0800
21,30
26.4 1
28.54
Q
( PSF>
I. 00
1.98
0,03897
2, 97
0.01623
3,95
0,01058
5.0 4
0 . 01029
0.00865
5.92
7 .00
REYNOLDS NUMBER/FOOT= 630372 .
MACH NUMBER=
,0 7
RPM= 2000
(R E
AND MACH NO, CALCULATED FR OM LAST POINT>
r
Ru n nUMber 2 4
WENTZ NACA
APRIL 12, 1 985
SNYDER -
PROP. DIA N.
VW
VT/VW
(FPS)
3 0.11
42. 5 3
52 . 0 4
60.03
67.04
73.38
7 9. :-:!2
8 ,7
6.16
5.03
4 . 36
3.91
3.57
3 . 31
T
NASA
LEWIS
64-621 POWERED ROTOR WITH BALANCE
(ft)
P
(lb)
Q
(f t-l b)
(WATTS)
2.8620
5.1600
6.9380
8 .1 340
8.6380
9 .1B BO
9.8000
-0.0900
0. 05 5 5
0.2805
0. 48 85
0.4540
0.41 45
0.428 0
-38.33
23.64
11 9 .4 7
208.06
193.37
176.54
182.29
~
1,667
CT
1 .3 0997
1 .1 8338
1 ,06288
0.93653
0.7974 7
0.7079 1
0.64784
CQ
CP
- 0.0 2 4 71
0. 00 764
0. 02578
o . 03374
0.02514
0.(}1916
(1.01697
-0.2 1492
0 . 04 70 1
0.12970
0.14717
0.09821
0 . 06836
0.05610
REYNOLDS NUMBE R/F OOT= 627548.
MACH NUMBER = . 069 6
RPM= 300 ()
(RE AND MACH NO , CALCULATED FROM LAST POIN T)
A23
Q
(PS F)
1. 00
2 . 00
2.99
3,98
4.9 6
S.9S
6 ,93
r
r~ Ufl
nUMbt~r
API~
25
PROP,
VW
VT/VW
( FPS)
3 0.16
42.S7
52.1 1
5 9 , 38
67,2
74. 25
79.S
I t 1. 2/
1905
WENTZ - SNYDER - NA SA L.EWI S
NA CA 6 4 - 6 2 1 POWERE D ROTOR WITH [lALANCE
T
<lb)
11. 58 3. 3 0 00
8,2
5.6440
6,7
8,0200
5 .88
9.7820
5.2
11.7920
4 ,7
13 ,3960
4.39 14, 5380
DIAM.
<ft)
'"
1.667
Q
P
(f't - lb)
( WA TTS )
- 0.187 5
-0 .1240
-106.48
1. 50552
-7 0 , 42
1. 292 04
4,83
1.22653
1.1510 6
1.08353
1.01 017
0.95619
0,0085
() , 172S
0.41 25
0. 68 35
O,868S
97 ,96
2 34 .26
3 88,16
493.22
CT
CQ
CP
Q
(PSF )
- 0 ,05 1 3 1
-0. 01 7 03
- 0 .59408
- 0,13965
1. 00
2.00
0,00078
Q.(J1 2 i 8
0,02274
0,0 0522
0,07159
3, 0 0
0,11814
3 . 89
4.99
O. 0309~?'
0.034 27
0 . 1 4539
0.15049
6. 9 7
6, 09
REYNOLD S NUMBER/FOOT = 627496.
MACH NU MBE R= , 0698
RPM = 4000
(R E AN D MA CH NO, CALC ULATED
FROM
LAST POIN T)
r
I~ur l
n UMbe r
AP RIL 12 , 1985
WEN TZ - SNYDER - NASA LE WI S
NACA 64-621 POW ER ED ROTOR WITH BALANCE
26
PROP. DI AM .
vw
VT/VW
(FP S )
30.22
14.44
42,61
10. 2 4
0,3&
7 .24
6.48
5 . 92
5 .4 8
52,2
60.2 4
67 .32
73 .72
79.6
T
(¥ t)
Q
P
( 1 b)
( ft -Ib)
( WAT TS )
9 02 0
6 .07 2 0
8 . 5 860
10. 9 460
13 . 0340
1 5. 146 0
16. 8340
- 0.28 5 5
-0 . 26 4 5
- 0,1970
-· 0.1005
0.0430
0. 222 0
0.4 235
-202. 67
~L
-187 . 76
-139 .84
-7 1. 34
3 0. 5 2
157.59
3 00.63
= 1. 667
CT
1,77222
1. 3878 t
1. 30997
1, 25 370
1.19543
1 . 158 3 3
1.10449
CQ
-
0. 07779
0 .03626
0,0180 3
0 .00691
0.00237
0.0101S
0,01667
CP
-
REYNOLDS NUM BE R/FOOT= 628176.
MACH NUMBER = .0699
RPM = sn no
(RE AND MACH NO. CA LCULAT ED FROM LAST POINT)
A24
1.12317
0. 37 14 6
0. 15075
0.05002
0.01 53 4
0.0 6029
0.09139
Q
(P S F)
1. 0 1
2 ,00
3 ,00
4 . 00
5,0 0
5 .99
6.98
r
R uri nUMber ?7
AP I~ r L 12 } 1985
WENTZ - SNYDEn - NASA LEWI S
NACA 64-621 POWERED ROTOR WITH BALANCE
PROP,
VW
VT/ VW
(FPS)
30. 29
42 . 67
T
<Ib)
is.aS
73.75
4.2560
11, 2S
6.3680
8.6980
9. 2
7.97 11.0640
7.06
13.6640
15 . 69 80
6.51
79 .63
6 .0 3
52.2
60.25
6 8. 0 1
1 7.6680
DIAM.
(f t )
Q
P
(ft-lb )
(WATTS)
-0.3395
- 0 . 3330
- 0.2810
- 0,2085
-0.09 4 0
-265.10
-260.0 2
-2 19 .42
- 162.8 1
-73.40
4 1. 7 8
168.66
0,0535
0 . 2160
= 1. 667
CQ
CT
CP
Q
(P SF)
1. 92793
1 . 45386
1. 32668
1. 2 66 9 3
1 .22798
1,19972
1. 158 18
-0.09226
-0,04 561
-0,0257 1
- 0,0 1432
- 0. 00 S 07
0,00245
0.00849
- 1.46203
-0.51310
- 0 . 23643
- 0 .1 1 4 12
- 0. 0 3577
0. 0 1 597
0 .05 121
1. 01
2.01
3. 0 0
4.00
5 .10
6 . 00
6.99
REYNOLD S NUMBER/FO OT= 628 423.
MACH NUMBER= . 0699
RPM=
550 0
(RE AND MACH NO. CALCULATED FROM LAST PO IN T>
RUri nUMber 28
APRIL 12 , 1985
WENTZ - S NYD ER - NASA LEWIS
NACA 64-621 POWERED ROTOR WITH BALANCE
PROP. DI AM.
vw
<FP S>
29.72
42.45
51.99
6 0. OS
67. 19
73
79.6
RPM
300
3200
3900
4500
5100
5 5 80
6 1 20
VT/VW
T
( LB)
.88
6.58
6.55
6.5 4
6 .63
6.67
6.71
(ft)
Q
= 1.667
CT
CQ
CP
.oos
,1902 1
.0014
.0 012 3
,0075
1 .1 640 3
7.646
.OOS
10.40B
12 .906
.0 1
.008 5
.0 055
.006
1.16928
1 .1 932 7
1,18392
1.21142
1.2 1845
.00 1 03
. 00046
.00069
. 000 4 7
.00679
.003
. 00 4 5
. 0 031
. 00 17 1
.408
5 .074
15.59
18 . 6 0 6
.00026
.00024
REYNOl.DS NU MBER/FOOT" 630 1 63.
MACH NUH BER = . 07
A25
Q
(P SF )
<FT- LB)
.00158
.98
2
3
4
4 . 99
5.9
7
Ron n UMb er 2 9
APIHL 1 2, 1 9 8 5
S N YD ER
NAS A LEWI S
2 30 24 PO W
ERED IW TO R WIT H [IALA NCE
WENTZ
NACA
-
-
PROP. DIAM.
VW
<FP S )
29 . 77
4 1 .09
Sl . 6 9
S9 . 69
66 . 7 4
73 . 1 13
79, OS
83 . 9 8
8 9 . '12
94. 5 8
RPM
VT / VW
11 70
1260
1 380
15 00
1 590
.7'
1. 0 2
1. 22
1. 32
1. 37
1.4
1. 3 9
1. 4 3
1. 4 6
1. 47
""
Q
T
(LIO
270
4 80
720
9 00
10 5 0
(f t )
1.66 7
CT
CQ
CP
Q
<PSF)
( F T - LB)
.364
.87 4
I. 522
, ODS
, 0 05
,DOS
2, 1 2 6
.OOS
2.722
3.332
3.86
4.4 8 4
,ODS
,00 65
,0 095
, OOB
5,186
.OOS
5 . 8 36
,DOSS
. 1 6975
. 001 4
,0 0 1 11
.98
. 21 437
. 236 34
.24755
. 25354
,0007 4
.00 07S
. 000 57
. 00046
. 00038
.0004 2
.00053
.000 41
1. 87
.25861
. 2 568
. 26 429
.2682 9
,27 171
.00047
.00035
. 00028
.00113
.00038
. 000 28
.000 16
.0 001 5
,00023
.0 00 2 3
2.95
3.93
4. 92
5.9
6. 8 9
7.7 7
8 .86
9.84
REYNO LDS NUMBER/FOO T= 72 7 790.
MACH NUMBER = .083
Run n UMbe r 31
APRIL 1 2 ,
1985
WENTZ - SNYDER - NASA LEWI S
NACA 2302 4 PO WE RED RO TO R WI TH BALAN CE
PROP. DIAM . ( ft>
VW
( FP S )
V T / VIJ
3 1,26
4 2 .1 2
51.5 9
5 17 . 6 2
66,66
73,02
7 8 .87
8 4 , :~2
0
0
0
0
0
0
0
0
0
0
8 8 , r/ 4
9 4, 36
r
Q
P
( 1b )
T
(ft-lb )
(WAT TS)
0 . 2 140
0.42 2 0
0.636 0
0. 8 42 0
1,0 62 0
1. 3 040
1 . 52 2 0
1, 758 0
1 .95 2 0
2 ,1 98 0
- 0 . 0070
-0 .0 1 00
- 0.0 100
- 0 ,0 1 40
-0,0 1 50
- 0.0150
- 0.0170
-0,018 5
-0,0200
- 0,0 2 00
0.0 0
0 . 00
0 . 00
0 ,0 0
0,00
0 . 00
0, 00
0.00
0 , 00
O. 00
= 1. 667
CT
CQ
Q
(P SF)
0. 09084
0.09851
0 . 09898
0,098 2 8
0. 0991 7
0, 1 014 7
0 , 10 151
0 .1025 9
0,10 239
0,10262
- 0 .0 0 178
- 0,001 4 0
- 0. 000 93
- 0 . 00098
- 0, 000 8 4
- 0, 000 7 0
- 0, 0 0068
-0 , 0 00 6 5
- 0. 00063
- 0,00056
REYNOLD S NUMBER/F OOT= 72 8 639 ,
HACH NUMB ER:: .0 82 9
RPM = 0
( RE AND MACH NO, CALCULA TED FROM LAST POI NT)
A26
CP
0 . 00000
0 . 00 000
0 .0 00 0 0
0.00000
0 ,00000
0 .00000
0,00 00 0
0 . 00000
0,0 00 0 0
0,00000
1. 08
I. 9 6
2 . 94
3, 9 3
4 , 91
5 , 89
6 . 87
7 , 85
8 , 73
9 ,8 1
I~un
nUM ber j 2
r
APR JL 12) 1985
WENTZ - SNY DEI?
NA SA LE WI S
NACA 2j 024 POWERE D ROTOR WITH BA LA NCE
-
PROP. DIAM.
VW
VT / VW
(FPS)
29.81
4 2 . 16
5 1. 6 3
59.62
66.66
7~L 09
80,06
84 . 39
89. 0 2
94.36
a
a
T
(Ib)
o .20 a a
0.3980
a .6100
0,7980
1,0 24 0
1. 2 4 00
1.4 900
1 .6640
1 .866 0
2. 0840
0
a
a
a
a
a
a
a
(ft)
Q
P
(ft-l b)
( WATT S )
- 0.0160
- 0.0300
- 0.0400
- 0 , 0500
- 0.0635
-0 .075 0
- 0.08511
-0.095 0
- 0.10 4 0
-0.1 150
0.00
o ,00
o ,00
0.00
0.00
0.00
a , 00
o . 00
0.00
0 . 00
= 1.
667
CT
CQ
CP
Q
( PSF)
0,09 339
0.092 92
0, 0949 4
0 ,09315
0.095 6 2
0,09649
0,09662
0.09712
0.09789
O. 09730
- 0.00448
- 0.004 20
-0,0 0373
- 0.00350
-0.0 0356
- 0.00 35 0
-0. 00331
- 0,00 333
-0. 00 327
-0,00322
0.00000
0 .00 0 00
0. 0 0000
0.00000
0. 0000 0
0,00000
0.00000
0. 00000
0.00 0 00
0.00 0 00
0.98
1. 96
2 . 94
3,93
4 .91
5 .89
7 . 07
7 , 85
8 .73
9,8 1
REYNOLD S NUHBER/FOOT= 728612,
MA CH NUM BE R= .0829
RP M::::
a
( RE AND MACH NO. CALCULATE D FR OM LAST POIN T)
Ru n nUMb e r 33
APRIL 18 , 1985
WENTZ - SNYDER - NASA LEWIS
NACA 23024 P OWERED ROTOR WIT H BA LAN CE
PR OP. DIA M.
r
VW
(FPS)
RPM
29 .84
41. 2 1
51.78
59. BS
66.91
73 .37
79 .25
8 4.8
89 .94
94.8 1
- 2 40
-330
- 40 5
-48 0
-540
-6 00
-66 11
-70S
- 75 0
- 795
VT/V W
T
(LB)
-, 7
- ,7
-.68
- ,7
-,7
-.71
-,73
-, 7 3
-,73
-,73
,286
, 572
, 896
1.1 98
1. 522
1.828
2. 144
2 .48
2.778
~L 098
( Tt)
=
1.667
CT
Q
CQ
CP
(F T-L B)
-.005
- • 0 liS
- ,005
- .005
- , 0 05
-, 009
- ,00 5
-.005
- ,005
- . DO S
, 133 46
.140 46
, 13935
.13 9 74
.14202
. 14 2 15
. 1 429
,14 463
. 14401
. 1445 4
-. 0 01 4
-,00 074
- ,00047
-. ()003 S
- ,00028
-.00042
-,0002
- .000 17
-.00016
- .00014
RE YN OLDS NUMBER/FOO T= 7 24 265.
MACH NUMBE R= . 0 832
A27
.0 0098
. 00051
.00032
. 00{)24
.00 02
,00 0 3
.00 015
.0001 3
, 00011
.000 1
Q
(P SF)
,9 8
1. 87
2 . 95
3.93
4. 9 1
5.B9
6.B7
7.86
8.8 4
9. 82
APR I L t U I
Ron n U Mtll:.! f ' 34
WENTZ
1905
SNYDER
NASA
-
-
LEWIS
NACI'! 64-621 PO We RED ROTOR WIT H BALANCE
PROP . DIAM,
VW
RPM
(LB)
42.49
7 20
72 0
52,02
720
30.07
60 .
as
67.19
73 , 6
79.49
84.98
9 0 . 62
94.99
T
VT /V W
(FP S)
2,09
1. 48
1. 21
1. OS
720
, 94
, 85
,79
,7'
,49
,64
72 0
720
72 0
720
720
720
,81
1. 242
1. 63
1.874
2, 164
2.462
2 .74
2,982
3 .1 94
3.406
( ft)
= 1,447
Q
CT
CP
CQ
Q
(PS F )
(FT-LIn
, 01
, 01
.0 14
,0175
.0 2
,025
,0 265
,03
.03 1
. 0345
REY NOLDS
.37 64 8
, 00 279
,28905
,2530 4
,21855
. 0 014
.0013
.20 17 3
. 191 29
,1 825 1
,99
,00583
,00206
.00122
.0011 2
,00128
1. 9 7
2.95
3. 9 ~5
.0010S
4 ,9 1
. 00117
.0 0106
,00099
,00 08 4
.00 1 57
.1738 2
,0 01 0S
, 00078
,1637
, 15887
,00 095
.000 97
.00066
.0006 4
5 .9
6 , 88
7 ,84
8.94
9,82
NUMBER/FOOT= 72 0960,
MACH NUMBER = .OB32
1~
un nUMb er
35
APRIL 18, 1 985
WENT Z - SNYDER - NASA LEWIS
NACA 64-621 POWERED ROTOR wIT H BALANCE
PROP, DIAM. (f t)
VW
VT /VW
(FP S)
30 .1 8
4 2.65
52,15
60 . 23
67 . 3
73 . 77
79,66
85 . 67
89 . 79
95 . 2 4
T
(lb)
5,78
4,0 9
3.35
2.9
2.59
2 , 37
2, 19
2.0 4
1. 94
1, 83
2.3480
3,7 2 40
4 , 2840
4,9360
5 .5 540
6 ,1 860
6.6 600
7 . 0620
7.51 2 0
7,9660
(RE
Q
P
(ft-lb)
(WA T TS)
0.0300
0.2170
0.1840
0.1690
0,1 380
8.52
61.62
52 . 25
47.99
39, 18
27.12
23 .14
22 .4 3
22,29
22.43
0, 0955
0.081.5
0,0790
0,0785
0.0790
= 1. 667
CT
CQ
Q
(PS F )
1.07883
O. BSB6 4
0,66065
0 ;57173
0 ,5 1513
0,47841
0.44175
Q.40 5 04
0 . 3 9221
0. 3 7029
0 , 008 27
0.0 3 001
0,01702
0 . 01174
0,0 076 8
0.00443
0,00324
0 ,0 0272
0 ,00246
0,00 220
REYNOLDS NUM BE R/ FOOT=- 720339,
MACH NUMDER = ,0833
RPM = 2 00 0
AND MACH NO. CALCULATED FROM L AST POINT>
A28
CP
0,04782
0. 1 2286
0 ,0 5498
0. 0340 4
0, 0 19 9 1
0 ,010 48
0,00 7 11
0.00554
0,00478
0,00404
1. 00
1. 99
2,97
3,96
4,9 4
5. 92
6.9 1
7 .9 9
8.78
9 .86
Ru r. nUMbe r' 36
AP IUL 18, 1905
SNY D [f~
NASA LE WI S
b4 - b2 1 POW eRE D ROTOR WITH BALA NCE
WENTZ
NACA
-
-
PROP, DIA M,
vw
(FP S )
21. 4
30 , 22
36. 9 7
42.69
47 , 68
52,25
60 , 2S
67.43
73 . 85
79.7 4
85.22
90 ,45
(;o5.B l
VT / VW
a ,16
5,78
4 .72
4 .0 9
3. 66
3,34
2 .9
2. 59
2.36
2 .1 9
2.05
1. 93
1, 82
T
Q
<l b)
(ft-lb)
1 ,38all
2. 40 00
3. 1720
3 , 7 80 0
4 ,0 740
4 ,3 440
4.44 2 0
5 , 64 2 0
6,2780
6,72 4 0
7 ,1 540
7 , 5360
7 , 970 0
- 0 , 044 5
0 , 03 4 0
0 , 14 00
0,2215
0. 19 4 0
0. 1900
0 . 0925
0, 1500
0 .1 350
0.09 2 0
0 . 0800
o,o so n
0 , 080 0
(f' t )
-- .\, b b 7
P
( WATTS)
- 12 ,6 4
9 , b5
3 9 ,75
62 , 89
55 .0 9
5 3,95
2 6. 27
4 2 ,5 9
3 8 ,33
26 , 12
22 , 72
2 2, 72
2 2,72
CT
1. 27 14 2
1,10230
0.9733 2
0,87137
0 . 752 7 8
0,66981
0 , 51499
0 .523 2 2
0. 4854 7
0 . 44 5 9 6
11 ,4 1538
0,38911
0. 3668 3
CQ
CP
- 0,02445
0.00937
0.02577
0.03063
0.02150
0,01757
0 , 00643
0,00834
0,00626
0.00366
0 ,00 279
0.00248
0,00221
- 0,19950
0,05 41 2
0,12169
0,12525
0.0787 2
0,058 7 2
0.01864
0,02160
0.01480
0.00 8 01
0.00 5 71
0.004 78
0,0040 2
Q
(P SF)
0,50
1. 00
1. 49
1. 9 9
2 ,48
2,97
3, 9 5
4,94
5 ,9 3
6, 91
7, 89
8 ,87
9 , 95
REYNOLD S NUM BER /FOOT= 72 171 7 ,
MACH NUMBE R= .0837
RPM :::: 20 0 0
'RE AND MACH NO, CALCULATED FROM LAST POINT)
Ro n
n UM b e r
37
APRI L 18, 1 9 0 5
NASA LEWI S
S NY D Er~
NACA 23 024 POWER ED ROTOR WITH BALANCE
WE NTZ -
-
PROP, DIA M, (ft )
vw
(FPS)
30 , 27
42 , 8 1
52, 3 9
60.53
67.6 4
7 4 .11
79 ,9 9
85 ,4 7
90 . 63
95 , 9 9
r
VT/VW
11. 5 4
8.1 6
6 , 66
5.77
S. 16
4.7 1
4 . 37
-'l.() 8
3.85
3. 6 4
T
Q
P
D b)
(f t -lb)
( WA TTS)
2 . 58 6 0
4,7940
6. 5 390
8.3300
9 ,80 6 0
10.49 60
10,81 8 0
11.45 80
12 . 22 60
13 .1040
- 0.11 6 0
- 0 , 01 65
0,1 28 0
0, 3230
0, 5330
0, 5595
0.304 5
0. 161 5
0 . 09 65
0.0 6 00
-65,8 8
- 9 ,37
7 2. 6 9
183,43
30 2 .69
317, 7 4
172 . 92
91,7 2
5 4 . 80
3 4.0 7
~
1,667
CT
1.18608
1.10094
1,00260
0.95874
0, 90372
0, 8 0737
0,7143 5
0,66260
0,62880
0.60083
CQ
CP
-0 .0319 2
-0 ,002 27
0,01177
0.02230
0.02947
O. 02582
0.01206
O.fl OS60
0.00298
0.00165
- 0.36817
-0 . 01854
0,07847
0,12863
0,15209
0.12163
0 .05265
O. fl228 tJ
0 .0 1147
0,0060 0
REY NOLD S NUMBER/FOOT= 722897 .
MAC H NUMBER= , OB39
RPM= 40 0 0
'RE AND MACH NO , CALCULATED FROM LA ST POINT)
1\29
Q
(PS F)
1. 00
2 . 00
2.99
3.98
4,97
5 ,96
6,94
7,n~
8,9 1
9,99
1<IJ r, n 'JM be r' 30
A PI~
-
WENT Z
.
J. L <.-. •. I
SNl'D Ek "
NA CA 23024 POWERE D
PROP. DIA M.
VW
VT / VtoJ
(FPS)
3 0.21
42 .613
So>;)
. . . . . . . L-
~~. >
60.3
68.06
73.86
79 .75
85.23
90.4 '7
9 5 ,35
T
<lb}
B.67
6.14
5.01
4.34
3 . 8S
3.SS
3.28
3.07
2. 8 9
2.7 5
2 .264 0
3 . 9620
5.1740
5,978 0
7,0300
7 .7080
8.3280
8 , 9600
9 . 5820
10,11 8 0
1 ';:; ~.;
l ~t,::. A
LEWIS
ROTOR WITH
(ft )
Q
P
(ft-lb)
(WA TTS)
- 0.0500
0 .1 055
0.1875
0,0770
0,0605
0. 0610
- 0. 0005
-0 ,0695
- 0.07 55
-O . OSSS
-2 1. 30
4 4. 93
79.86
32.80
25.77
25 .98
- 0,21
-29. 6 0
- 32.16
-23 ,64
•
[IA L ANe !..:
1,667
CT
CQ
CP
Q
( PSF)
1 . 04 08 9
0 . 9 1271
0.7 9 6 1 3
0,69 10 7
0. 6 379 f:!
0.594 98
0 . 55 1 40
0.5 1936
0. 4 9390
0.46956
- 0.01379
0,0 1458
0.0173 1
0 . 0 053 4
0 . 0032 9
0 ,0 02 8 2
- 0,00002
-·0.002 42
- 0 ,0 0233
- 0, 00 155
- 0. U 9 54
0.08946
0.0 867 9
0,02319
0. 01 267
0.010 0 1
- 0.00007
- 0 , 00742
- 0,00676
- 0,0042 4
1. 00
1. 99
2.98
3.96
5,05
5.94
6.92
7,90
8.89
9.87
REYN OLDS NUMBER/FOOT= 726215,
MACH NUMBER= ,0839
RP M= 3000
(RE AND MA CH NO, CALCULATED FROM LAST POINT)
II
Ru n nUMber 39
APRIL 22/ 1 985
wENTZ - SNYDER -
NASA
LE wI S
NACA 23 024 POWERED ROTOR wI TH BALANCE
PROP. DIA M. (f t )
VW
VT / VW
(F P S)
3 0.24
42.75
5 2 .3
60, 41
67.52
74
80,47
85,4
'JO.56
96
T
<lb)
8.66
6,13
5 .01
4 . 33
3 ,8 B
3 .54
3 . 25
3.07
2.89
2 . 73
2.2880
3.8420
4, 986 0
5 .99 2 0
6.9540
7.764 0
8.568 0
9.0360
9,6560
10. 2340
Q
p
(f t -lb )
( WATTS)
- 0, 085 0
0.0300
- 0,0 1 05
- 0.0770
- 0.045 5
-0.0100
0 .0480
- 0.048 5
-0.037S
0,0020
-36. 2 0
1 2.78
- 4 ,47
-32.80
- 19,38
-4,26
20 .44
-20,66
-IS.97
0.85
= 1.667
CT
CQ
CP
1. 0517 4
0 . 8854 6
0,7 6 756
0. 69267
0 , 64362
0. 5 9926
0 . 5 5923
0.52 373
0. 49769
0,47 0 24
- 0 . 0 23 44
0. 0 04 15
- 0.00097
- 0 . 00534
- 0.00253
- 0.00046
0. 0 0188
- 0.0 01 69
-0.0 011 6
0 . 000 06
- 0 , 2 02 97
0.02541
-0, 00485
- 0,023 1 4
- 0,0 0980
- 0,0 01 64
0, 00 6 12
- 0,00517
- 0 .0033'5
0 .0 0 0 15
REYNOLD S NUMBER/FOO T", 725902.
MACH NUMBER = , 0843
RP M= 3 0 0 0
(RE AND MACH NO. CALCULA TED FROM LAS T PO INT>
I
A30
Q
(PSF)
1. 00
1. 99
2.98
3 ,96
4.9 5
5.94
7.02
7 .91
8,89
9.97
Ruri nU Mber 40
APR I L 221 1905
WrNTl.
SNYDER
NA SA L. EWI S
NACA 2 3 02 4 rOW E.nE D !-IOTOR WITH BALANCE
-
-
PROP. DIAI'I.
VW
( FPS)
VT/VW
3 0.28
42.77
52. 4
60 . 4 7
8.65
6. 12
5
4 . 33
3.B7
3 . 53
3.27
3.06
2.89
2 .74
6'/.58
74. 0 7
79.9 ('/
85 .48
90 . 6 4
C)5.62
r
<1b)
2.1660
3.7040
4. 94 2 0
6.0160
6. 91 8 0
7 . 8700
8.68 20
9. 184 0
9.68 0 0
10.31 60
(tt )
Q
p
( ·f't-lb)
(WATTS)
-0.1250
- 0. 1425
- 0.3120
-0.3080
- 0. 27 20
-0 .2 1 05
- 0.1 2 8 5
- 0.134 0
-0.14 6 0
-0. 11 05
- 5 3. 2 4
- 60 . 69
-13.2.89
- 13 1 . 18
- 11 5 . 85
-8('/ . 66
-54.73
- 57.07
-62.18
- 47.0 6
~
1.667
cr
CQ
CP
Q
( PSF)
0.99656 -0. 03450
0 . 854 1 0 -0. 01971
0.76087 - 0.028 82
0.695 4 2 -0 . 02136
0.64032 . - 0.01510
0.60736 - 0 . 00 975
0 . 57462 - 0.00 51 0
0.53223 - 0 . 004 6 6
0. 4 98 91 -0. 00451
0. 47868 -0 . 00308
- 0 . .2 9833
- 0.120 6 7
- 0 .14401
-0. 09 2 4 9
- 0.05852
- 0. 03445
- 0 . 01670
- 0 .014 27
-0. 01304
-0 . 00842
1. 00
1. 9 9
2.98
3.96
4 . 95
5 .94
6.92
7 .91
8.89
9.87
REYNOLDS NUH BER/FOOT= 72 11 65.
MACH NUM BE R= .0839
RPM = 3000
(RE AND MAC H NO. CA LCULATED FR OM LAST POINT)
Ru rl nUMb e r 41
APRIL 221 1985
WEN TZ - SNYDER - NASA LEWIS
NA CA 6 4-621 POWERED ROTO R WIT H BALANCE
PROP. DIAM.
VW
(F PS )
VT / VW
3 0. 37
4 2. 9
5 1 . 66
60.62
67. '/9
74 .2
80 . 67
8.62
6 .1
5. 07
4,32
85 . 6
3. U6
90.77
2,88
2,7 4
clS .6S
r
3, 86
3.53
3.25
(ft)
r
Q
P
<1 b )
( ft-l b)
(W A TTS)
2 ,6880
4.8260
6 . 29 60
7 . 74 4 0
8.6060
9.026 0
9.7880
10 .27 4 0
10. 0 34 0
11 . 3360
- 0.0 9 00
0 ,0600
0 . 25 05
0 , 4 830
0, 52 10
0 .44 05
0. 4 815
0.4 9 00
0.4 8 10
0.4560
-38. 33
25 .56
10 6, 69
2 05 .7 2
221.90
187.62
2 05.0 0
2 0F].70
204.87
194 ,22
~
1.667
cr
1 ,231 92
1 . 10 816
0.99884
0.8 9228
0.79455
0 .69557
0 . 638 03
0.5 9479
0 . 5578 6
0.5256 1
CQ
CP
- 0.02474
0 . 00826
0 .0 238 4
0 . 03338
0,02886
0,0203 6
0.0188 3
0. 01 7 02
0 .014 86
0 . 01 26 8
-0.2 1335
0. 05 04 4
0.12083
0.144 20
0.1114 6
0,0718 7
0,06111
0. 052 05
0 . 04 286
0.0347 2
REYNOL DS NUM BE R/F OOT= 72 140 2 .
MAC H NUMBER"" ,0839
RPM ::: 3000
(RE ~ND MACH NO . CALClll.ATE D FROM LAST POINT)
;,,3 1
Q
(PSF )
1. 00
2 .0 0
2.89
3.98
4 .96
5 .95
7 . 03
7 ,9 1
8 . 90
9 . 88
A I' 1<[ L
~~;;I
I
19U5
Uf\l YVER _. NAGA LEWI S
64 - 62 1 PUWE RU) ROTOR WIT H BAL ANCE
WEN I Z NA C A
PR() P. DIA M.
VW
( FP$ )
V T /VW
3 0.38
42 . 89
52 . 52
6 0 .6
67 . 77
74 . 2
BO.l0
BS. 1 6
9 0 . 86
9 6.23
8.62
6 .1
4.99
4.32
3. 86
3.53
3.27
3. 07
2.88
2.72
T
(lb )
2.760 0
4.6800
6.16 60
7 . 370 0
8.3260
9 . 0380
9.7880
10. 4 080
11 . 0980
11 .8 4 80
( ·ft }
Q
p
(ft - lb)
(WATTS )
-0. 09 95
0.052 5
O. ~~ 4 3 5
0.4295
0.52 2 0
0.5040
0.4845
0.4 5 35
0.4125
0.4041)
- 42.38
22.36
103. 71
182.9 3
222 .33
214.66
2 06. 36
193 .1 6
17 5. 69
172 . 07
.- t . 6 6 7
Cl
1.26424
1.0 7522
0 .9 464 3
0 .84978
0.76902
0.69648
0.64 705
0 . 61002
0. 57132
0.543 75
CP
CQ
- 0.02 7 34
0.00724
0.0 22 4 2
0.0 29 7 1
0 .0 28 92
0 . 02330
0 . ()i9 21
0 . 0 1594
0. 01 274
0.0 111 2
-·0 . 23568
0.04417
0 .1 1 177
(l. t 2836
0.11175
o . 08222
0. 06274
0.049 03
0 . 03671
0. 03026
Q
(P SF)
1. 00
1. 99
2 . 99
3 .97
4.96
5.95
6.93
7 . 82
8.90
9 . 98
REYNOLDS NUM BE R/FOOT = 722880.
MACH NUMB ER= .0843
RPM ::: 3000
( RE AND MACH NO. CALCUL ATED FRO M l.A ST POINT)
Rurl nUM be r' 4 3
WENTZ
-
221 1985
AP rU t
-
SNYDER
NA S A LEWIS
NACA 6 4- 62 1 POWERED ROTOR wITH BALANCE
PR OP . DIAM.
VW
( FPS)
VT/VW
3 0. :39
4 2 .92
8.62
6. 1
4 . ~;8
4.3 2
3.86
3 . 53
3.24
3, tl6
2 .88
2.73
5 ~~ .
S6
60 .64
6 7 .7 5
74 . 2 5
80 .74
05 .69
9 0 .86
(15. 8 4
T
( 1 b)
2.67()0
4.5 14 0
6.0240
7. 09130
7 .9 2 40
8 . 7460
9.6 7 40
1 0, ~~620
11. 0260
11 . 6800
(ft)
P
Q
(f'"t-lb )
(WATTS)
-0 .1 240
0.0075
0 . 1775
0.3540
0.3 6 40
0.3100
0 .3050
0.3005
0.3070
0 . 3 220
-52 .81
3,1 9
75.6 0
150.78
155.04
132 .04
129.91
127.9 9
13 0.76
137 .15
-- 1.667
CT
1.2238 4
1.03773
0.9249 6
0.81 883
0.73 233
0.6 7423
0.6 3 068
0.5998 3
0.S676 5
0.5414 2
CQ
CP
- 0 ,034 10
0 .00103
0.016 35
0,0 2 4 5 0
0,0 2 0 18
0.01434
0.01193
0 . 01044
0.00 9 48
0.008 95
-0. 29373
0.0063 1
0,08145
0.10578
0 . 077 9 9
0,0 5 05 6
0.0 3 868
0.03189
0 .02732
0.02446
RE YN OLDS NUMB ER/ FOOT= 7 18115 .
MACH NUM[iER= . 0839
RPM = 30 00
CI~E
AND MACH NO. CALCUl.ATED FROM l.AST POI NT)
A32
Q
(P SF)
1. 00
1. 9 9
2.98
3.97
4.96
5 .94
7 . 03
7.92
8 .90
9.88