february 17, 20051 aerodynamics 2 pdr michael caldwell jeff haddin asif hossain james kobyra john...
TRANSCRIPT
February 17, 2005
1
Aerodynamics 2 PDR
Michael CaldwellMichael CaldwellJeff HaddinJeff Haddin
Asif HossainAsif HossainJames KobyraJames KobyraJohn McKinnisJohn McKinnis
Kathleen MondinoKathleen MondinoAndrew RodenbeckAndrew RodenbeckJason TangJason TangJoe TaylorJoe TaylorTyler WilhelmTyler Wilhelm
AAE 451: Team 2AAE 451: Team 2
February 17, 2005
2[ 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 ]
Overview
3-View Drawing Airfoil Selection Wing & Tail Geometry Control Surface Sizing & Effectiveness Twist Distribution Mathematical Model Launch Conditions L/DMAX & Endurance
February 17, 2005
3[ 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 ]
Aircraft 3-View
Mission Requirements
15 min. endurance
Take-off distance ≤ 60 ft.
Vstall ≤ 15 ft./s
Vloiter ≤ 25 ft./s
35 ft. turn radius
February 17, 2005
4[ 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 ]
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
SELIG 1210 AIRFOIL
Airfoil Selection: Wing
February 17, 2005
5[ 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 ]
WORTMANN FX 63-137
Wortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel
Airfoil Selection: Wing
February 17, 2005
6[ 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 ]
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 DataWortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel
Airfoil Selection: Wing
February 17, 2005
7[ 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 ]
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
8[ 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 ]
Airfoil Selection: Wing Wortmann FX 63-137
Lift Curve
-0.5
0
0.5
1
1.5
2
-10 -5 0 5 10 15 20
Alpha (deg)
Cl
XFOIL (Re=100800)
XFOIL (Re=155600)
Experimental (Re=100800)
Experimental (Re=155600)
Wortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel
February 17, 2005
9[ 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 ]
Airfoil Selection: Wing
Wortmann FX 63-137: M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel
Wortmann FX63-3137Drag Polar
-0.5
0
0.5
1
1.5
2
0 0.02 0.04 0.06 0.08 0.1 0.12
Cd
Cl
XFOIL (Re=100800)
XFOIL (Re=155600)
Experimental (Re=100800)
Experimental (Re=155600)
February 17, 2005
10[ 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 ]
Airfoil Selection: Wing
FX-63-137 XFOIL data
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
20,000 40,000 60,000 80,000 100,000 120,000 140,000
Reynolds number
CL
max
CLmax vs. Re
February 17, 2005
11[ 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 ]
Airfoil Selection: Canard
NACA 0012
February 17, 2005
12[ 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 ]
Airfoil Selection: CanardNACA 0012 Lift Curve
-2
-1.5
-1
-0.5
0
0.5
1
1.5
2
-10 -5 0 5 10 15 20 25
Alpha (deg)
Cl
XFOIL (Re=98000)
XFOIL (Re=150000)
'XFOIL (Re=3000000)
Experimental (Re=3000000)
Abbott, I.H. & A.E. von Doenhoff, “Theory of Wing Sections”
February 17, 2005
13[ 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 ]
Airfoil Selection: CanardNACA 0012Drag Polar
-1.5
-1
-0.5
0
0.5
1
1.5
2
0 0.01 0.02 0.03 0.04 0.05 0.06
Cd
Cl
XFOIL (Re=98000)
XFOIL (Re=150000)
XFOIL (Re=3000000)
Experimental (Re=3000000
Abbott, I.H. & A.E. von Doenhoff, “Theory of Wing Sections”
February 17, 2005
14[ 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 ]
Airfoil Selection: Vertical Tails
Flat Plate Non-Lifting Surface No Volume Needed Ease of Construction Light Weight
February 17, 2005
15[ 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 ]
Geometry
Wetted Area : 9.013 ft2
Wing Canard Vertical Tail (Individual)
Area (ft2) 5.24 1.2 0.64Chord (ft) 1 0.67 1.00Span (ft) 5.24 1.8 0.64
Aspect Ratio 5.24 2.69 0.64Taper Ratio 0.7 0.7 1
Dihedral Angle 4o -4o 0o
Sweep Angle 0o 0o 45o
February 17, 2005
16[ 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 ]
Control Surfaces: Aileron
Span: 2.26 ft Chord: 0.2 ft Area: 0.45 ft2
-20 -15 -10 -5 0 5 10 15 20-0.25
-0.2
-0.15
-0.1
-0.05
0
0.05
0.1
0.15
0.2
0.25AILERON force vs. Deflection
Deflection (deg)
AIL
ER
ON
fo
rce
(lb
s)
15 ft/s
22 ft/s
AIL
ER
ON
forc
e (lb
f)
February 17, 2005
17[ 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 ]
Control Surfaces: Rudder (Single)
Span: 0.57 ft Chord: 0.35 ft Area: 0.20 ft2
-20 -15 -10 -5 0 5 10 15 20-0.8
-0.6
-0.4
-0.2
0
0.2
0.4
0.6RUDDER force vs. Deflection
Deflection (deg)
RU
DD
ER
fo
rce
(lb
s)
15 ft/s
22 ft/s
RU
DD
ER
forc
e (lb
f)
February 17, 2005
18[ 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 ]
Control Surfaces: Elevator
Span: 1.8 ft Chord: 0.23 ft Area: 0.42 ft2
-20 -15 -10 -5 0 5 10 15 20-0.8
-0.6
-0.4
-0.2
0
0.2
0.4
0.6ELEVATOR force vs. Deflection
Deflection (deg)
EL
EV
AT
OR
fo
rce
(lb
s)
15 ft/s
22 ft/s
ELE
VA
TO
R fo
rce
(lbf)
February 17, 2005
19[ 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 ]
Wing Twist Distribution
Root: 0.35o
Tip: -6.48o
February 17, 2005
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 ]
Wing Twist Distribution
*Neglecting Parasite Drag
*
February 17, 2005
21[ 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 ]
Mathematical Model
From Prandtl’s Classical Lifting-Line Theory
*LLL CCCo
615.0oL
C 1deg067.0 L
C
io DDD CCC 030.0
oDC
eAR
CC LDi
2
44.1cos9.0 25.0maxmax clL CC
February 17, 2005
22[ 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 ]
Mathematical Model
Re=147,820
February 17, 2005
23[ 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 ]
Mathematical Model
*MMM CCCo
087.0oM
C 1deg0.00025 M
C
2
2
cos2
cos
AR
ARCC
airfoilmoM
* Raymer, Daniel P., Aircraft Design: A Conceptual Approach p.493
February 17, 2005
24[ 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 ]
Mathematical Model
February 17, 2005
25[ 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 ]
Launch Conditions
Vtake-off = 1.2Vstall = 18 ft/s Climb Angle = 20o
Angle of Attack = 4.5o
αLo = -9.12o
February 17, 2005
26[ 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 ]
L/DMAX
L/DMAX=10.75
αL/Dmax=0.60o
Re=147,820
February 17, 2005
27[ 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 ]
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
28[ 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 ]
Endurance
-6 -4 -2 0 2 4 6 8 10 120
5
10
15
20
25
30Endurance with Brushed Motor
Angle of Attack [deg]
End
uran
ce [
min
]
Brushed Motor
Brushless Motor
Re=147,820
Assumptions Level Flight No Acceleration Loiter~Straight Time =
Loiter~Turning Time
February 17, 2005
29[ 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 ]
Summary
3-View Drawing Airfoil Selection Wing & Tail Geometry Control Surface Sizing & Effectiveness Twist Distribution Mathematical Model Launch Conditions L/DMAX & Endurance Questions?
February 17, 2005
30[ 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 ]
Appendix
February 17, 2005
31[ 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 ]
Mathematical ModelNo Wing Twist: Re=147,820
February 17, 2005
32[ 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 ]
Wing Twist Distribution