Project Dragonfly
Tony Waymire (TL)
Peter Parmakis
John Barthe
Jason Mickey
Tyler Gillen
Andy Betourne
Purpose





High-performance aerobatics
Low drag
Low cost
Two seat trainer capability
Satisfy all LSA requirements
Waymire
2
Competition
Extra 200
1
Max Speed
154 kts
MTOW
1770 lbs
Power
200 HP
Cost
$ 250,000
Su-31
2
3
Max Speed
220 kts
MTOW
2420 lbs
Power
360 HP
Cost
$ 190,000
Waymire
3
Configurations
John Barthe
Responsibilities


Determine Internal and External
Layout
Find CG locations



For crew configurations
For fuel configurations
Design CAD Model
Barthe
5
Configuration Down-Selection
Barthe
6
Configuration Down-Selection
Barthe
7
Component and CG Locations


Engine (RED)
Crew Compartment



(BLUE)
Tandem Seating
Fuel
(GREEN)
Sensor hub (PINK)
Barthe
8
Tractor
Barthe
9
Twin Boom
Barthe
10
Pusher
Barthe
11
Future Work




Modification of internal structure
and landing gear
Addition of control surfaces
Detailed model of propulsive
system, cabin compartment, and all
tertiary components
Further refined CG location
Barthe
12
Performance
Andy Betourne
Responsibilities




Mission profile
Constraint analysis
Power required
Turn performance
Betourne
14
Desired Requirements
Stall Speed
45 knots
Cruise Altitude
5000 feet
Maneuver Altitude
4000 feet
Power Required
38 Hp at 120 knots
Gee load
-3 to 6
Betourne
15
Mission Profile

Acrobatic mission

Maneuver near airfield
Betourne
16
Mission Profile

Ferry Mission

Maximize range
Betourne
V L Wi 1
R
ln(
)
CD
Wi
4
17
Constraint Diagram
Design Point
Specified cruise
0.5
Take-off
Best cruise
0.45
0.4
Stall speed
Land
P/W
0.35
0.3
Sustained Turn Rate
0.25
0.2
0.15
0.1
0.05
0
0
5
10
15
20
25
W/S
Betourne
18
Power Required
50
45
40
35
30 'd
req
25
20
15
10
5
0
P (Hp)
P
0
2
1
W
 V 3SCD 
( 1 )
2
o 1 VS  eAR
2
20
40
60
80
100
120
V (knots)
Betourne
19
Turn Performance
Psi dot (deg/sec)
140
g n 1

V
120

100
80
60
2
n=2
n=3.5
n=5
n=6.5
n=8
40
20
0
60
80
100
120
Velocity (knots)
Betourne
20
Future Work


Take-off and landing analysis
Detailed turn analysis


Climb and dive performance
Roll and loop feasibility
Betourne
21
Aerodynamics
Tyler Gillen
Responsibilities




Determine wing size and shape
Choose sample airfoil for
calculations
Extract lift and drag coefficients for
various stages of flight
Ensure stall speed requirements are
met
Gillen
23
Wing Sizing and Layout


Take weight and wing loading
numbers to get wing area. Initially
S=110 ft2
High-,Mid-, or Low-wing? 5



Mid-wing reduces dihedral effect
Mid-wing reduces interference drag
No wing dihedral used
Gillen
24
Wing Sizing and Layout cont.

No wing quarter-chord sweep


No wing twist used



Aft sweep leads to tip stall, increases weight
Could be used to maintain aileron effectiveness
Leads to increase in manufacturing cost
Aspect Ratio=6


2
Looked into similar aerobatic planes and many
used this value
Higher AR is more efficient, had higher
(L/D)max but stalls at lower angle of attack
Gillen
25
Wing Sizing and Layout cont.

Taper Ratio=.45


l=.45 gives lift distribution closest to
ideal 5
l=.4 would be best for weight 5
Gillen
26
Airfoil Selection



Looked into aerobatic, other
symmetrical airfoils
Analyzed all candidates with XFOIL
program
Chose NACA 2412 6
Gillen
27
Lift and Drag Coefficients

Determined lift and drag coefficients
using XFOIL and methods in Raymer
and Roskam 8 9
All
Config. Pusher
Twin
Boom
Puller
CD
CD
Configuration
CL
Cruise (@ 108 kts)
0.30
0.0150 0.0174 0.0151
Landing (@ 55 kts with
20 deg of flaps)
1.17
0.1088 0.1132 0.1098
Takeoff (@ 55 kts, no
flaps)
0.99
0.0724 0.0755 0.0732
Gillen
CD
7
28
Stall Speed Requirement




Needed to increase wing area to
meet stall speed requirement
Requirement: maximum stall speed
is 45 kts
Increased area to S=125 ft2
Vs=44.8 kts
Gillen
29
Resulting Wing shape
Gillen
30
Future Work



Employ numerical methods to
determine lift to a greater accuracy
and get spanwise lift distribution
Component by component lift and
drag breakdown
Research and choose an aerobatic
airfoil to meet requirements
Gillen
31
Stability and Control
Tony Waymire
Responsibilities




Initial tail sizing
Control surface sizing
Neutral point calculations
Static margin
Waymire
33
Tail Dimensions 10
Horizontal
Stabilizer
Pusher
Puller
Twin boom
Elevator
Pusher
Puller
Twin Boom
Span (ft)
Chord (ft)
10.7
9.13
7.31
2.5
2.5
2.5
10.7
9.13
7.31
1.125
1.125
1.125
Waymire
34
Tail Dimensions 10
Vertical
Stabilizer
Pusher
Puller
Twin boom
Rudder
Pusher
Puller
Twin Boom
Span (ft)
Chord (ft)
5.14
5.5
4.38
2.5
2.5
2.5
5.14
5.5
4.38
1
1
1
Waymire
35
Neutral Point / Static Margin


Neutral point
calculated using
Raymer 10
Power on neutral
point not yet
available
Power Off Static
Margin (%)
Config.
Pusher
1
2
Pilot Pilots
1.93
9.60
Puller
3.33
6.98
TwinBoom
4.17
5.99
Waymire
36
Future Work



Trim analysis
Turn rate analysis
Tail size trade studies
Waymire
37
Structures
Peter Parmakis
Responsibilities




Fuselage Structures
Wing Structures
Landing Gear
V-n Diagram
Parmakis
39
Fuselage Structures





Ring support
Longerons
Skin
Load Paths
Materials
Parmakis
40
Wing Structures 11, 12




Spar
Ribs
Skin
Materials
Parmakis
41
6-gee Wing Loads
Parmakis
42
-3-gee Wing Loads
Parmakis
43
Landing Gear 11


Tail Dragger
Prop and tail strike
Parmakis
44
V-n Diagram 13


Max positive load: 6 gees
Max negative load: -3 gees
Parmakis
45
V-n Diagram
Positive Load
6 gees
Negative Load
-3 gees
Positive Maneuver
Velocity
109.7 knots
Negative Maneuver
Velocity
74.8 knots
Minimum Cruise
Velocity
107.2 knots
Minumum positive
stall speed
44.8 knots
Minimum negative
stall speed
43.2 knots
Dive speed
150.1 knots
Parmakis
46
Future Work




Advanced structural analysis (FEM)
Detailed structure sizing
Component-wise material selection
Landing gear positioning
Parmakis
47
Propulsion
Jason Mickey
Propulsion Considerations




Required Power vs. Available Power
Propeller Sizing
Engine Weight
Fuel Consumption
Mickey
49
Power Available
Need at least 38 HP
Engine
Power (HP)
Rotax 582 UL
14
53.6
Rotax 912 UL
15
79.0
Jabiru 2200
85.8
16
Mickey
50
Thrust vs. Velocity
1000
900
Rotax 582 UL
Rotax 912 UL
Jabiru 2200
800
Thrust (lbf)
700
600
500
400
300
200
100
0
0
20
40
60
80
100
120
Velocity (kts)
Mickey
51
Propeller Sizing 17

Choose smaller of:
D  Kp  4 Power
Vtip
D
2  n
60
Mickey
Engine
RPMs
Propeller
Diameter
(ft)
Rotax
582 UL
6000
4.49
Rotax
912 UL
5800
4.72
Jabiru
2200
3300
4.82
52
Engine Weight
Want to maximize Power-toweight ratio
Engine
Engine
HP
Weight (lbs) per lb
Rotax 582
UL
79.2
0.677
Rotax 912
UL
121.3
0.651
Jabiru 2200
138.0
0.622
Mickey
53
Fuel Consumption
Want to minimize fuel consumption
Engine
Fuel Consumption at
75% Power (Gal/hr)
Rotax 582 UL
4.76
Rotax 912 UL
5.0
Jabiru 2200
3.96
Mickey
54
Future Work



Propeller selection
Finalized engine selection
Detailed Fuel Consumption
Mickey
55
Conclusion


Viable market
Conventional pusher




Tail dragger
Split vertical tail
Tandem seating
High Durability
Mickey
56
References





[1]http://www.avbuyer.com/aircraftsales/Aircraft
Results.asp?ListId=4&AircraftManufacturerId=1160
&subList=1240&NumberPerPage=10 [retrieved 4
November 2008]
[2] “Extra 200: Two Seat Advanced Aerobatic
Trainer,” Extra Aircraft, LLC,
http://www.extraaircraft.com/media/EA200.pdf
[retrieved 4 November 2008].
[3]http://snaproll-sukhoi.com/su31specs.htm
[retrieved 4 November 2008].
[4] Raymer, D., “Sizing from a Conceptual Sketch,”
Aircraft Design: A Conceptual Approach, 4 ed., AIAA,
Virginia, 2006, pp. 15-28.
[5] Roskam, J., “Wing Layout Design,” Airplane
Design: Part III: Layout Design of Cockpit,
Fuselage, Wing and Empennage: Cutaways and
Inboard Profiles, Roskam Aviation and Engineering,
Ottawa, KS, 1989, pp. 163-239.
57
References




[6] Selig, M., UIUC Airfoil Coordinates Database
[online database], http://www.ae.uiuc.edu/mselig/ads/coord_database.html [retrieved 1
November 2008].
[7] Raymer, D., “Aerodynamics,” Aircraft Design: A
Conceptual Approach, 4 ed., AIAA, Virginia, 2006,
pp. 303-354.
[8] Roskam, J., “Drag Polar Prediction Methods,”
Airplane Design: Part VI: Preliminary Calculation of
Aerodynamic, Thrust and Power Characteristics,
Roskam Aviation and Engineering, Ottawa, KS,
1990, pp. 21-113.
[9] Roskam, J., “Lift and Pitching Moment Prediction
Methods,” Airplane Design: Part VI: Preliminary
Calculation of Aerodynamic, Thrust and Power
Characteristics, Roskam Aviation and Engineering,
Ottawa, KS, 1990, pp. 213-353.
58
References




[10] Raymer, D., “Stability, Control, and Handling
Qualities,” Aircraft Design: A Conceptual Approach,
4 ed., AIAA, Virginia, 2006, pp. 467-508.
[11] Raymer, D., “Structures and Loads,” Aircraft
Design: A Conceptual Approach, 4 ed., AIAA,
Virginia, 2006, pp. 389-450.
[12] Ishai, O. and McDaniel, I.M., “Appendix A:
Material Properties,” Engineering Mechanics of
Composite Materials, 2nd ed., Oxford, NY, 2006, pp.
373-383.
[13] Roskam, J. “4.2 Methods for Constructing V-n
Diagrams,” Airplane Design Part V: Component
Weight Estimation, Lawrence, KS, 1989, pp. 31-34.
59
References

[14]http://www.leadingedgeairfoils.com/pdf/582info.pdf
[retrieved 4 November 2008].

[15]http://www.rotaxservice.com/documents/912inf
o.pdf
[retrieved 4 November 2008].

[16]http://www.jabirupacific.com/specs/2200.htm

[retrieved 4 November 2008].
[17] Raymer, D., “Propulsion and Fuel System
Integraion,” Aircraft Design: A Conceptual
Approach, 4 ed., AIAA, Virginia, 2006, pp. 221-257.
60
Questions?
61
62
63
64