C.P. No. 1150
MINISTRY OF DEFENCE (PROCUREMENT EXECUTIVE)
AERONAUTICAL
RESEARCH COUNCIL
CURRENT
List of Current
the Aeronautical
PAPERS
Papers
published
Research
Council
Nos. 1101-1150
LONDON.
HER MAJESTY’S
STATIONERY
1972
PRICE 17p NET
for
OFFICE
C.P. No.1150
List
of Current papers
publlshed
for
THE AEXONAUTICALRESEARCHCOUNCIL
(Numbers 1101 - 1150)
and placed on sale by H.H. Stationery Offloe
:.P. No.
Council No.
1101
31 277
Normal shock wave tables for air,
argon, carbon dioxide. carbon
monoxidr, i-ydrogen, nitrogen,
nitrous oxlne and oxygen.
(June, 1969).
Lapworth, K. C.
1102
29 913
Prelzminary flight
assessment
of the low-speed handling of the
BAC 221 ogee-cng research
aircra' t.
(November, 1967).
Barnes, C. S.
and
Nxholas, 0. P.
1103
30 083
A wind-tunnel uwestlgation
of
the stalling
performance of
two conpressor cascades of
different
a:;Iect ratios at
low speed.
(March, 1968).
Shaalan, M. R. A.
Title,
Publxation
1104
etc.
Author(s)
discont.!nued.
1105
30 846
Lor-epeed flight
tests on a
tailless
delta wing azrcrafX
(Avro 707B) nlth wings swept
back L&5*, Part 2 Longitudinal
stability
and
control.
(August, 1967).
Port,
W. G. A.
end
Morrall,
J. C.
1106
22 242
Low-s?eed fl,ght
tests on a
tailless
delta nlng arcraft
(Avro 707B) alth wings swept
back 44.5". Part 3 Longltudlnal
stability
end
control.
(April,
1960).
Perry, D. ii.,
blorrall, J. C.
and
Port, H. G. A.
-2-
I
C.P. NO. /Council
!
No.
Title,
etc.
Author(s)
1107
22 256
Low-speed flight
tests on a
tailless
delta wing aircraft
(Avro 707B) with wings swept
back k&.5'=. Part 4 - Wing flow.
(April,
1960).
Perry, D. H.,
Port, W. G. A.
end
Morrall, J. C.
1108
30 636
Low-speed. wind tunnel tests on
an unswept wmg-fuselage model
of ascect ratlo 9.0 nlth
tangentud blowrng over
trailing-edge
flaps and aileron?.,
ncludug
the effect ofsllpstream.
(May, 1968).
Lawford, J. A.
1109
31 311
Influence of wing root shaping on
the pressure dlstrlbutlon
of
swept-wing body ConfiguratIons.
(July. 1969).
Brtigerater,
J.
and
Wilson, K. H.
1110
31 285
The estwatlon
of the loading on
swept rings with extending chord
flaps X-I subsonic speeds.
(February,l969).
YcKie, J.
1111
jo
Interim note on tests with
mounted fan nacelle with
fan Jet simulated by cold
blonlng and alternatively
gas generating shroud.
(March, 1968).
Pauley, G
1112
31 161
An outline guide to criteria
for
the limitation
of urban noise.
(March, 1969).
Robinson, D. W.
1113
31 966
Gust response measurements on
* mdel aircraft.
(December, 1969).
Cansdale, R.
and
Hall, H.
1114
31 474
IngestIon of debris into
intakes by vortex action.
(December, 1968).
Glenny, D. E.
158
wing
the
air
by a
-3-
C.P. No.
Council No.
I/
etc.
Author(s)
I
I
I
1115
Title,
31 064
Some observatmns on the heat
transfer characterlstlcs
of a
rotatmg mred c0nvect10n
thermosyphon.
(March,
1969).
of
W. D.
1116
31 266
Non-equilibrium
carbon dioxide
(June, 1969).
1117
31 468
An 1nvestlgat~on of the stresses
in a wind tunnel corner section.
(February, 1969).
D. E. W.
and
Baxter, P. S. A.
1118
34 344
Low-speed characteristxcs
Keating, R. F. A.
and
Mayne, B. L.
waverider
(March,
emissivity
near L3P.
I-Morris,
of
wings.
1969).
Hodgson, J. P.
Stone,
Ill9
32 146
Operational and theoretical
studies on the effect of pIlot
actlon on heavy landings.
(December, 1969).
1120
32 122
Vertical
acceleratron in the
Kltchell,
cockpit of a subsonx transport
alrcrsft
durmg take-off maasured
during a1rllne o;Kratml.
(October, 1969).
1121
3I
The use of cross-correlation
and
power spectral techniques for
the ulentlficatxn
of the
Hunter bk.12 dynamc response.
(July, 1969).
Fry, D. E.
1122
31 II8
Tests on a hlach number of 2.0
on a rectangular,
twin-duct
au intake with variable
geometry, situated m the flow
field of B slender wmg.
(December, 1768).
Dobson, Y. D.
1123
32 032
An mvestlgatmn
of the scatter
in variable-amplitude
fatiguetest results of 2024 and 7075
Stagg, A. M.
760
materials.
(w,
1969).
Hall,
H.
and
Hutton, G. B.
C. G. B.
-4-
:.p.
No.
1124
:ounc11 No.
31 816
Title,
etc.
Author(s)
Algol pro@-a-s
for the response
analysts of 11nca.r systems with
determll+stu:
or random uwuts.
(July. $963).
1
Hazlewood, L. J.
and
Huntley,
E.
1125
31 771
Super VC 10 ,ruue drag.
A wind-tunnel uweutlgatlon,
Part 1 ExDerlmental
techniques.
(August, 7969).
Taylor, C. Ft.,
Hall, J. R.
and
Hayward, R. Ei.
1126
31 445
The role of heat conduction in
leadln& ed&,e heating theory
and experxents.
Nonweller, T.
Wang, H. Y.
and
Aggarwal, S. R.
(June,
1969).
1127
30 986
Llquld and vapour cooling
for gas turbines.
(November, 1969).
systew
Edwards, 3. P.
112%
31 725
Temperattie and fluid urooerty
effects on cavitation
irk
arcraft
fuel pumps.
(August. '769'.
Lester,
1129
31 588
Delta wnlngs ulth longitudinal
camber
et low soeed.
(September, 1969).
Nangm, R. K.
and
Hancock, G. J.
1130
32 237
Experuwntai
mvest:gatmn
of
the effect of trailing-edge
sweepback on the subsonic
longitudinal
characterxt;cs
of slender wmg.s.
(March, 397(:).
KIrkpatrick
D. L. I.
and
Hepworth, A. G.
W. G. S.
-5-
c..P. No.
C:ouncil
No.
Title,
etc.
Author(s)
r
1131
31 724
Results and analysis of pressure
measurements on two isolated
slender wngs and slender nlngbody conbblnatlons at suoersonio
speeds.
(November, 1969).
Fellows, K. A. (Mrs)
and
h-t&r,
E. C.
1132
32 232
A compressive test specimen for
unidirectconal
carbon fibre
reinforced plastics.
(JaI"wY,
1970).
fsins,
P. D.
1133
32 287
Interference
effects at M = 8.5
of wires and probes on the wake
of a magnetically
suspended
rounded base cone.
(February, 1970).
ksne,
J. F. W.
1134
32 330
Sore flxght and rind-tunnel
longitudinal
stability
measurements on the BAC 221
slender-wing aircraft.
(April,
1970).
aarnes, c. s.
and
ioss. R.
1135
32 354
Civil Aircraft
Airworthiness
Un(ing,G. E.
Data Recording Programme special.
events relating
to au-speed
control and handling (January 196t
to February, 1969)
(January, 1970).
1136
31 984
Airflow rate requirements
passenger aircraft.
(November, 1?69),
1137
32 143
Subsonlc theoretical
lift-curve
slope, aerodynemic centre and
spsnwise loading for arbztrary
aspect ratlo, taper ratlo and
sweepback.
(May, 1970).
in
Cimby, E. A.
hrner, H. C.
and
Sandra Y. Inch.
-6-
Title,
Author(s)
etc.
Fliaht tests to invastlaate
the
problems of steep &x&aches
by JTQL aircraft.
(December, 1969).
O'Leary, c. 0.
and
Setter,
N. V.
Experlwntal
verifxcatlon
of
predIcted static hole sire
effects on a model with large
streamwise
pressure
gradients.
(February, 1970).
Pugh, P. G.,
Pete, J. W.
and
Ward, L.C.
iYin+tunnel
tests at transonic
and supersonic speeds to
investigate
the longitudinal
stability
of a model of the
Avro 720 aircraft.
(May, IV@).
Huntley,
Some observations on vortex
shedding and acoustic
resonsnces.
(January, 1970).
Gaster.
A hovel method for the estlmatlon
of the zero-lift
forebody
pressure drag of axisylmnetric
non-slender shapes at
supersonic and hypersonic
velocitxs,
(February, 1970).
Pugh, P. G.
and
Ward, L. C.
A numer~.csl procedure for
constructing
shock-nave
envelopes around conical bodies
using data from schlleren
photographs.
(August, 1970).
Larcombe, M. J.
Parameter astimatlon for the
log-nonral parent population of
fatigue failures from a sample
containing both failed and
non-failed members.
(August. 1970).
Staa,
B.
M.
A. lb.
-7-
:.P.
No.
:ouncil
No.
Title,
etc.
Author(s)
1145
30 682
Two-dimnsional
low-speed tunnel
tests on the NACA 0012 section
including measurements made
during pitching osclllatlons
et the stall.
(h'ay, 196A).
Moss, G. F.
and
Murdur, P. id.
1146
31 702
Progress report on observations
of thres-dxnenszonal flow patterns
obtained during stall development
on aerofolls,
and on the problem
of' measurrng two-dlmenuional
charactwizt:cs.
(Januard, ?37C).
G~gory,
Qurncey,
O'Kexlly,
and
Hall, D.
1147
31 067
The dirft of an auto-p:lot
gyroscope 2~ to prolonged
acceleration
y1 the Skylark
rocket.
(September. 196a)
Knott,
1148
30 997
Gun tunnel force measurements
on some thin tielta wings
suitable for hycersonlc cruising
flight.
(February, 1969).
Opatonskl,
Vibration levels experznced
in take-off on a large
Plexlble alrcraf3.
Hall,
1149
32 600
(July,
1150
I9@).
Lxt of Current Papers publlshed
for the Aeronautical Research
Council. Ncs. 1101 - 1150.
N.,
V. G.
C. L.
J.
F. R.
T.
I
K.
C.P. No. 1150
C.P. No. 1150
\BN II 4703% 1