Download Team2-Aerodynamics2PDR

Aerodynamics 2 PDR
AAE 451: Team 2
Michael Caldwell
Jeff Haddin
Asif Hossain
James Kobyra
John McKinnis
February 17, 2005
Kathleen Mondino
Andrew Rodenbeck
Jason Tang
Joe Taylor
Tyler Wilhelm
1
Overview
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February 17, 2005
3-View Drawing
Airfoil Selection
Wing & Tail Geometry
Control Surface Sizing & Effectiveness
Twist Distribution
Mathematical Model
Launch Conditions
L/DMAX & Endurance
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
2
Aircraft 3-View
February 17, 2005

Mission Requirements

15 min. endurance

Take-off distance ≤ 60 ft.

Vstall ≤ 15 ft./s

Vloiter ≤ 25 ft./s

35 ft. turn radius
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
3
Airfoil Selection: Wing
SELIG 1210 AIRFOIL
Selig 1210: M.S.Selig,J.J.Guglielmo,A.P.Broeren and P.Giguere,"Summary of Low-Speed Airfoil Data, Volume 1 – Wind Tunnel Data
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
4
Airfoil Selection: Wing
WORTMANN FX 63-137
Wortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
5
Airfoil Selection: Wing
SELIG – WORTMANN COMPARISON
Selig 1210: M.S.Selig,J.J.Guglielmo,A.P.Broeren and P.Giguere,"Summary of Low-Speed Airfoil Data, Volume 1 – Wind Tunnel Data
Wortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
6
Airfoil Selection: Wing
Wortmann FX67-137
Wortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
7
Airfoil Selection: Wing
Wortmann FX 63-137
Lift Curve
2
1.5
Cl
1
XFOIL (Re=100800)
XFOIL (Re=155600)
Experimental (Re=100800)
Experimental (Re=155600)
0.5
0
-10
-5
0
5
10
15
20
-0.5
Alpha (deg)
Wortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
8
Airfoil Selection: Wing
Wortmann FX63-3137
Drag Polar
2
1.5
Cl
1
XFOIL (Re=100800)
XFOIL (Re=155600)
Experimental (Re=100800)
Experimental (Re=155600)
0.5
0
0
0.02
0.04
0.06
0.08
0.1
0.12
-0.5
Cd
Wortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
9
Airfoil Selection: Wing
CLmax vs. Re
FX-63-137 XFOIL data
2
1.8
1.6
1.4
CLmax
1.2
1
0.8
0.6
0.4
0.2
0
20,000
40,000
60,000
80,000
100,000
120,000
140,000
Reynolds number
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
10
Airfoil Selection: Canard
NACA 0012
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
11
Airfoil Selection: Canard
NACA 0012
Lift Curve
2
1.5
1
Cl
0.5
0
-10
-5
0
5
10
15
20
25
-0.5
-1
XFOIL (Re=98000)
XFOIL (Re=150000)
'XFOIL (Re=3000000)
Experimental (Re=3000000)
-1.5
-2
Alpha (deg)
Abbott, I.H. & A.E. von Doenhoff, “Theory of Wing Sections”
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
12
Airfoil Selection: Canard
NACA 0012
Drag Polar
2
1.5
1
Cl
0.5
0
0
0.01
0.02
0.03
0.04
0.05
0.06
XFOIL (Re=98000)
XFOIL (Re=150000)
XFOIL (Re=3000000)
Experimental (Re=3000000
-0.5
-1
-1.5
Cd
Abbott, I.H. & A.E. von Doenhoff, “Theory of Wing Sections”
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
13
Airfoil Selection: Vertical Tails
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Flat Plate




February 17, 2005
Non-Lifting Surface
No Volume Needed
Ease of Construction
Light Weight
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
14
Geometry
Area (ft2)
Chord (ft)
Span (ft)
Aspect Ratio
Taper Ratio
Dihedral Angle
Sweep Angle
Wing
Canard
Vertical Tail
(Individual)
5.24
1
5.24
5.24
0.7
4o
o
0
1.2
0.67
1.8
2.69
0.7
-4o
o
0
0.64
1.00
0.64
0.64
1
0o
o
45
Wetted Area : 9.013 ft2
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
15
Control Surfaces: Aileron
AILERON force vs. Deflection
0.25
15 ft/s
22 ft/s
0.2

force
AILERON
AILERON
force(lbf)
(lbs)
0.15
0.1
0.05

0
-0.05

-0.1
Span: 2.26 ft
Chord: 0.2 ft
Area: 0.45 ft2
-0.15
-0.2
-0.25
-20
February 17, 2005
-15
-10
-5
0
5
Deflection (deg)
10
15
20
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
16
Control Surfaces: Rudder (Single)
RUDDER force vs. Deflection
0.6
15 ft/s
22 ft/s
RUDDER force (lbs)
RUDDER force (lbf)
0.4

0.2
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0
-0.2
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Span: 0.57 ft
Chord: 0.35 ft
Area: 0.20 ft2
-0.4
-0.6
-0.8
-20
February 17, 2005
-15
-10
-5
0
5
Deflection (deg)
10
15
20
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
17
Control Surfaces: Elevator
ELEVATOR force vs. Deflection
0.6
15 ft/s
22 ft/s
ELEVATOR
ELEVATOR force
force (lbf)
(lbs)
0.4

0.2

0
-0.2
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Span: 1.8 ft
Chord: 0.23 ft
Area: 0.42 ft2
-0.4
-0.6
-0.8
-20
February 17, 2005
-15
-10
-5
0
5
Deflection (deg)
10
15
20
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
18
Wing Twist Distribution
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
February 17, 2005
Root: 0.35o
Tip: -6.48o
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
19
Wing Twist Distribution
*
*Neglecting Parasite Drag
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
20
Mathematical Model

From Prandtl’s Classical Lifting-Line Theory
C L  C Lo  C L * 
C Lo  0.615 CL  0.067 deg 1
C D  C Do  C Di
C Do  0.030
C L2
C Di 
eAR
CLmax  0.9Clmax cos  0.25c  1.44
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
21
Mathematical Model
Re=147,820
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
22
Mathematical Model
 AR cos 2  

CM  Cmoairfoil 
2
 AR  2 cos  
CM  CM o  CM  *
1
CM o  0.087 CM  0.00025 deg
* Raymer, Daniel P., Aircraft Design: A Conceptual Approach p.493
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
23
Mathematical Model
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
24
Launch Conditions
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


February 17, 2005
Vtake-off = 1.2Vstall = 18 ft/s
Climb Angle = 20o
Angle of Attack = 4.5o
αLo = -9.12o
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
25
L/DMAX


L/DMAX=10.75
αL/Dmax=0.60o
Re=147,820
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
26
L/DMAX
L/DMAX Velocity
 Loiter Straight:


VL/Dmax= 21.97 ft/s
Loiter Turn:

VL/Dmax= 23.12 ft/s
Re=147,820
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
27
Endurance
Endurance with Brushed Motor
30
Assumptions

Level Flight

No Acceleration

Loiter~Straight Time =
Loiter~Turning Time
25
Endurance [min]
20
15
Brushed Motor
Brushless Motor
10
5
0
-6
-4
-2
0
2
4
6
Angle of Attack [deg]
8
10
12
Re=147,820
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
28
Summary

3-View Drawing
Airfoil Selection
Wing & Tail Geometry
Control Surface Sizing & Effectiveness
Twist Distribution
Mathematical Model
Launch Conditions
L/DMAX & Endurance

Questions?
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February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
29
Appendix
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
30
Mathematical Model
No Wing Twist: Re=147,820
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
31
Wing Twist Distribution
February 17, 2005
[ Overview | 3-View | Wing 1 2 3 4 5 6 7 | Canard 1 2 3 | Tails | Geometry | Control Surfaces 1 2 3 | Wing Twist 1 2
| Mathematical Models 1 2 3 4 | Launch Conditions | L/Dmax 1 2 | Endurance | Summary | Appendix 1 2 ]
32