March 1, 20051 Aerodynamics 3 QDR Michael Caldwell Jeff Haddin Asif Hossain James Kobyra John...
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March 1, 2005 1 Aerodynamics 3 QDR Michael Michael Caldwell Caldwell Jeff Haddin Jeff Haddin Asif Hossain Asif Hossain James Kobyra James Kobyra John McKinnis John McKinnis Kathleen Mondino Kathleen Mondino Andrew Rodenbeck Andrew Rodenbeck Jason Tang Jason Tang Joe Taylor Joe Taylor Tyler Wilhelm Tyler Wilhelm AAE 451: Team AAE 451: Team 2 2
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Transcript of March 1, 20051 Aerodynamics 3 QDR Michael Caldwell Jeff Haddin Asif Hossain James Kobyra John...
March 1, 2005
1
Aerodynamics 3 QDR
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
March 1, 2005
2[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Overview
3-View Drawing Launch Conditions Revisited Control Sizing Revisited Trim Diagram Control Derivatives
March 1, 2005
3[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Mission Requirements
15 min. endurance
Take-off distance ≤ 60 ft.
Vstall ≤ 15 ft/s
Vloiter ≤ 25 ft/s
35 ft. turn radius
Aircraft 3-View
March 1, 2005
4[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Launch Conditions Revisited
αLo = -9o
Vtake-off = 1.2Vstall = 18 ft/s Climb Angle = 20o
Angle of Attack = 4.5o
-9o
20o
4.5o
March 1, 2005
5[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
X-Plot Revisited
March 1, 2005
6[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Sizing Revisited
Class 1 Sizing
Class 2 Sizing
Canard Area Sht
1.43 ft2 1.36 ft2
Vertical Tail
Area Svt (each) 0.92 ft2 0.91 ft2
March 1, 2005
7[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Sizing Revisited
Span (ft) Chord (ft) Area (ft2)
Aileron (each)
1.40 0.20 0.28
Elevator 1.00 0.33 0.33
Rudder (each) 0.75 0.58 0.44
March 1, 2005
8[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Effect of Control Surface Deflection: Lift
CTL ic cL L c L cC C i C
ic c
cL c L
SC C
S
1 slipc
cc
Sx
S
c ic c
L LC a C
'L
c Theory
Theory c l
l Cb l
l l C
aC ka K C
C C a
Roskam,Jan, Airplane Design PartVI: Prelimenary Calculation of Aerodynamic, Thrust, and Power Characteristics, 2000
March 1, 2005
9[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Effect of Control Surface Deflection: Pitching Moment
ctl ic cM M c M cC C i C
ic cM L c cC C V
c
cc ac cg
SV x x
S
c ic c
M MC a C
Roskam,Jan, Airplane Design PartVI: Prelimenary Calculation of Aerodynamic, Thrust, and Power Characteristics, 2000
March 1, 2005
10[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Trim Diagram
CL Max Trimmed Maximum CL
(xref = xcg)
α CL Max
α = 0o
March 1, 2005
11[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Variation of Yawing Moment Coefficient with Sideslip Angle
VBWnnnn CCCC
13.57 radb
l
S
SKKC BB
RNns
lB
1sincos
radb
ZlCC VV
ynVV
11
rad
S
S
d
dkCC V
VLyVV
04.0n
CRoskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977
March 1, 2005
12[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Variation of Rolling Moment Coefficient with Sideslip Angle
VHWBllll CCCC
1
44 tan
tan3.57
2
rad
CC
CK
C
C
CKK
C
CCC
c
l
cZl
l
M
l
AL
l
fML
l
LlW
c
WBWB
b
HHll S
bSCC
HBH
1sincos
rad
b
lZCC VV
ylVV
06.0l
CRoskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977
March 1, 2005
13[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Variation of Pitching Moment Coefficient with Elevator Angle
HLH
Lm VCc
lCC
FEE
b
C
C
l
LlL K
C
CCC
l
L
M
M
FF
|
|
16.0E
mC
Roskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977
March 1, 2005
14[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Variation of Yawing Moment Coefficient with Rudder Deflection
b
lZCC VV
ynRR
sincos
S
SKKCC VbC
C
CLy l
l
L
VR'
03.0R
nC
Roskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977
March 1, 2005
15[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Variation of Rolling Moment Coefficient with Aileron Deflection
RLAlll CCC
09.0A
lC
Roskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977
March 1, 2005
16[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Summary
3-View Drawing Launch Conditions Revisited Control Sizing Revisited Trim Diagram Control Derivatives
Questions?
March 1, 2005
17[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Appendix
March 1, 2005
18[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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
March 1, 2005
19[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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
March 1, 2005
20[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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
March 1, 2005
21[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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
March 1, 2005
22[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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
March 1, 2005
23[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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)
March 1, 2005
24[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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
March 1, 2005
25[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Airfoil Selection: Canard
NACA 0012
March 1, 2005
26[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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”
March 1, 2005
27[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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”
March 1, 2005
28[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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
March 1, 2005
29[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Airfoil Selection: Vertical Tails
Flat Plate Non-Lifting Surface No Volume Needed Ease of Construction Light Weight
March 1, 2005
30[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Mathematical ModelNo Wing Twist: Re=147,820
March 1, 2005
31[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Wing Twist Distribution
March 1, 2005
32[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Wing Twist Distribution
*Neglecting Parasite Drag
*
March 1, 2005
33[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Wing Twist Distribution
Root: 1o
Tip: -7o
March 1, 2005
34[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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
March 1, 2005
35[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Mathematical Model
Re=147,820
March 1, 2005
36[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Mathematical Model
*MMM CCCo
087.0oMC
1deg0.00025 MC
2
2
cos2
cos
AR
ARCC
airfoilmoM
* Raymer, Daniel P., Aircraft Design: A Conceptual Approach p.493
March 1, 2005
37[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
Mathematical Model
March 1, 2005
38[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
L/DMAX
L/DMAX=10.75
αL/Dmax=0.60o
Re=147,820
March 1, 2005
39[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
L/DMAX
L/DMAX Velocity Loiter Straight:
VL/Dmax= 21.97 ft/s
Loiter Turn: VL/Dmax= 23.12 ft/s
Re=147,820
March 1, 2005
40[ Overview | 3-View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]
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
