1. Team 5 Aerodynamics PDR #2
Scott Bird
Mike Downes
Kelby Haase
Grant Hile
Cyrus Sigari
Sarah Umberger
Jen Watson
November 18, 2003
Aero PDR #2

2. Preview Airfoil Sections and Geometry Aerodynamic mathematical model
Launch Conditions
Endurance
November 18, 2003
Aero PDR #2

3. Walk-Around Data Boom Conformal Pod Engine Landing Gear
November 18, 2003
Aero PDR #2

4. Aircraft 3-view
November 18, 2003
Aero PDR #2

5. Wing Geometry Wing Airfoil NACA 2412 Aspect Ratio 7 Span 14 (ft)
Chord (ft)
Planform Area (ft^2)
Taper Ratio (deg)
Dihedral (deg)
Sweep Angle (deg)
November 18, 2003
Aero PDR #2

6. Horizontal Tail Geometry
Airfoil NACA 0012
Aspect Ratio 5
Span (ft)
Chord (average) (ft)
Planform Area (ft^2)
Taper Ratio
Sweep Angle (deg)
November 18, 2003
Aero PDR #2

7. Vertical Tail Geometry
Airfoil NACA 0012
Aspect Ratio 2
Span (ft)
Chord (average) (ft)
Planform Area (ft^2)
Taper Ratio
Sweep Angle (deg)
November 18, 2003
Aero PDR #2

8. Used XFOIL to get NACA 2412 2-D data
Lift Methodology
Used XFOIL to get NACA D data
Converted 2-D data to 3-D data for wing CLo and CLα
Used XFOIL to get NACA 0012 horizontal tail data
Used method described in Roskam Part VI, CH8 for CLδe
November 18, 2003
Aero PDR #2

9. Aerodynamic Mathematical Model of Lift
CL= CLo + CLα * α + CLδe * δe
CLα = Cl α / (1 + (Cl α / (π * e * A))) [rad-1]
CL = Cl * (CLα/Cl α)
CLδe = CLα_ht * ηht * Sht / Sref * τe [rad-1]
ηht = f (Sht_slip, Sht, Pavailable, U, Dp, qbar)
(Roskam Part VI, CH8)
November 18, 2003
Aero PDR #2

10. Aerodynamic Mathematical Model of Drag
Summation of individual components for CDo
Wing, fuselage, horizontal tail, vertical tail
CD=CDo + k * CL * CL
CDo = Σ CDo(i)
CDo(i) = (Cf * FF * Q * Swet) / Sref
k = 1 / (pi * AR * e)
CDo(i)
CDo_wing
0.0104
CDo_horizontal tail
0.0039
CDo_vertical tail
0.0013
CDo_fuselage
0.0204
CDo_total
0.036
November 18, 2003
Aero PDR #2

11. Moment Methodology
Used method described in Roskam, Chapter 3 of AAE 421 Book to find individual components of moment equation
November 18, 2003
Aero PDR #2

12. Aerodynamic Mathematical Model of Moments
CM = CMo + CMα * α + CMδe * δe
(α and δe in degrees)
CM0 = Cmac_wf + CL0_wf*(xbar_cg - xbar_acwf) + CLalpha_h*eta_h*(S_h/S)*(xbar_ach - xbar_cg)*epsilon
CMalpha = (x/cw)*CLalpha_wf*(xbar_cg - xbar_acwf) - CLalpha_h*eta_h*(S_h/S)*(xbar_ach - xbar_cg)*(1 – depsilon/dalpha)
CMdele = -CLalpha_h*eta_h*Vbar_h*tau_e
November 18, 2003
Aero PDR #2

13. Aerodynamic Mathematical Model Summary
CL= (rad-1)* α (rad-1)* δe
α and δe are in radians
CD = * ( (rad-1) * α)2
Cm= * α * δe
November 18, 2003
Aero PDR #2

14. Launch Conditions Known Values W = 49.6 lbs S = 28 ft2
ρ = slug/ft3 (at 600 ft)
CLmax:To = 0.8*CLmax = 1.44
VTO = 39 ft/s
November 18, 2003
Aero PDR #2

15. Launch Conditions from EOM
Normal
Drag
Thrust
Our Airplane
Friction
Weight
November 18, 2003
Aero PDR #2

16. Launch Conditions from EOM integration
STO = 76 ft
Constriant of 127 ft
tTO = 3.7 s
November 18, 2003
Aero PDR #2

17. Endurance Known Values Bhp = 3.7 hp ηp = 0.40 Cbhp = 0.0022 lb/s-hp
Wi = 49.6 lbf
Wf = 43.6 lbf
Using 1 6 lbf
L/D = 10.39
12*.866 (86.6% of L/Dmax when Vmin power)
November 18, 2003
Aero PDR #2

18. E = 75.5 minutes Endurance V = [2*W/( ρ*S)*(K/(3*CDo))1/2] ½
(Raymer, eq 17.33)
K = 1 / ( pi * AR * e )
power = 32.5 ft/s
E = (L/D)*[(550*ηp)/(Cbhp*V)]*ln(Wi/Wf)
(Raymer eq 17.31)
E = 75.5 minutes
November 18, 2003
Aero PDR #2

19. Resize flaps for landing Verify known values Cbhp
Future Work
Resize flaps for landing
Verify known values
Cbhp
Weight reduction from extra fuel (Endurance)
November 18, 2003
Aero PDR #2

20. Review of Today’s Presentation
Wing Geometry and Size
3-view of aircraft
Aerodynamic mathematical model
Launch Conditions
Endurance
November 18, 2003
Aero PDR #2

21. Questions
Questions??
November 18, 2003
Aero PDR #2

22. References Roskam Raymer AAE 251 Book AAE 421 Book
Aircraft Design: A Conceptual Approach
AAE 251 Book
Introduction to Aeronautics: A Design Perspective
November 18, 2003
Aero PDR #2

23. Putting EOMs into MATLAB
Put state space EOMs into MATLAB
Used ode45 command to integrate EOMs
Inputs to the code are initial conditions for position and velocity
Used x(0) = 0.1ft and v(0) = 1ft/s to eliminate singularities
Code output position and velocity as a function of time
November 18, 2003
Aero PDR #2

24. EOM file in MATLAB
November 18, 2003
Aero PDR #2

25. November 18, 2003
Aero PDR #2