1. Team 5 Aerodynamics PDR Presented By: Christian Naylor Eamonn Needler Charles Reyzer

2. 2 AAE 451 – Team 5 February 17, 2005 Outline Airfoil Sections Wing/Tail Geometry, Areas Mathematical Models Incidence Angles Control Surfaces Endurance

3. 3 AAE 451 – Team 5 February 17, 2005 Airfoil Sections – Wing Wing  Eppler E212 Tail  Eppler E169 Horizontal Tail  NACA 0010 Vertical Tail

4. 4 AAE 451 – Team 5 February 17, 2005 Geometry – Wing Sizing  Weight : 0.6 lbs  W/S: 0.38 lbs/ft 2  Wing Area: 1.58 ft 2 Geometry Simplification  2 Trapezoid Sections

5. 5 AAE 451 – Team 5 February 17, 2005 Geometry – Wing Defined Sweep Angles (Λ) Defined taper ratio (λ) of 1 st segment Defined Span Ratio of 2 segments Adjust to balance  Style  Aspect Ratio  Tip Chord feasibility

6. 6 AAE 451 – Team 5 February 17, 2005 Geometry – Wing Find Mean Aerodynamic Chord and Aerodynamic Center:

7. 7 AAE 451 – Team 5 February 17, 2005 Geometry – Tail Define Tail Volume Coefficients based on similar aircraft:  C vt = 0.04  C ht = 0.50 Find tail areas  S vt =c vt bS/L vt = 0.20 sq ft  S ht =c ht cS/L ht = 0.47 sq ft

8. 8 AAE 451 – Team 5 February 17, 2005 Geometry – Wing

9. 9 AAE 451 – Team 5 February 17, 2005 Mathematical Model

10. 10 AAE 451 – Team 5 February 17, 2005 Mathematical Model – Lift Prandtl Lifting Line Theory 1 Elliptical Lift Distribution 1 Anderson, J.D., Fundamentals of Aerodynamics, New York, 2001, pp 351-416

11. 11 AAE 451 – Team 5 February 17, 2005 Mathematical Model – Lift Spanwise Γ DistributionSpanwise Downwash Distribution Span (ft) w(y) (m 2 /ft 2 s) Γ (y) (m 2 /s)

12. 12 AAE 451 – Team 5 February 17, 2005 Mathematical Model – Lift Curve Spanwise Lift Coefficient DistributionLift Coefficients vs. α α (deg)Span (ft) C L and C l CLCL Max Lift at Cruise α: 0.74 lbf C Lmax (Hembold): 0.74 Max Lift (Hembold): 1.10 lbf

13. 13 AAE 451 – Team 5 February 17, 2005 Mathematical Model – Drag Calculated from Lifting Line Theory 1 e=0.75 1 Anderson, J.D., Fundamentals of Aerodynamics, New York, 2001, pp 351-416 CLCL CDCD Drag Polar

14. 14 AAE 451 – Team 5 February 17, 2005 Mathematical Model – Moment Pitching Moment vs. α α (deg) C M and C m 2 Raymer, D.P., Aircraft Design: A Conceptual Approach, Virginia, 1999, pp 315-378,493-494

15. 15 AAE 451 – Team 5 February 17, 2005 Mathematical Model – L/D L/D max =11.89 Cruise at α=3° α (deg) L/D L/D vs. α

16. 16 AAE 451 – Team 5 February 17, 2005 Incidence Angles Span (ft) αiαi Spanwise Induced α

17. 17 AAE 451 – Team 5 February 17, 2005 Control Surfaces Ailerons  50% to 90% on span  15% to 25% of chord  Used junction to 95% chord and 25% of chord Elevator  0% - 90% on span  25% to 50% of chord  Used 75% of span and 50% chord Rudders  Same typical ranges as elevators  Used 10% to 90% on span and 50% chord

18. 18 AAE 451 – Team 5 February 17, 2005 Control Surfaces Sizes  Aileron Area: 0.082 ft 2 (each)  Elevator Area: 0.176 ft 2  Rudder Area: 0.039 ft 2 (each)

19. 19 AAE 451 – Team 5 February 17, 2005 Endurance  Battery Wgt. Fraction = 0.064  Battery Weight = 0.038 lbs.

20. 20 AAE 451 – Team 5 February 17, 2005 Future Work Revisit Sizing Code Revisit Aerodynamic Center/ CG Calculations Revisit Spanwise Lift Distribution Look at Trade Studies