Aerodynamics 3 QDR AAE 451 Team 2 Michael

Aerodynamics 3 QDR AAE 451: Team 2 Michael Caldwell Jeff Haddin Asif Hossain James Kobyra John Mc. Kinnis March 1, 2005 Kathleen Mondino Andrew Rodenbeck Jason Tang Joe Taylor Tyler Wilhelm 1

Overview n n n 3 -View Drawing Launch Conditions Revisited Control Sizing Revisited Trim Diagram Control Derivatives March 1, 2005 2 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

Aircraft 3 -View Mission Requirements n 15 min. endurance n Take-off distance ≤ 60 ft. n Vstall ≤ 15 ft/s n Vloiter ≤ 25 ft/s n 35 ft. turn radius March 1, 2005 3 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

Launch Conditions Revisited n n αLo = -9 o Vtake-off = 1. 2 Vstall = 18 ft/s Climb Angle = 20 o Angle of Attack = 4. 5 o 20 o -9 o March 1, 2005 4 [ 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 5 [ 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 Vertical Tail Area Svt (each) 1. 43 ft 2 1. 36 ft 2 0. 92 ft 2 0. 91 ft 2 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 Aileron (each) Elevator Rudder (each) Span (ft) Chord (ft) Area (ft 2) 1. 40 0. 28 1. 00 0. 33 0. 75 0. 58 0. 44 March 1, 2005 7 [ 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 Roskam, Jan, Airplane Design Part. VI: Prelimenary Calculation of Aerodynamic, Thrust, and Power Characteristics, 2000 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: Pitching Moment Roskam, Jan, Airplane Design Part. VI: 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 ]

Trim Diagram CL Max Trimmed Maximum CL (xref = xcg) α CL Max α = 0 o March 1, 2005 10 [ 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 Roskam, Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977 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 Rolling Moment Coefficient with Sideslip Angle Roskam, 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 Pitching Moment Coefficient with Elevator Angle Roskam, 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 Yawing Moment Coefficient with Rudder Deflection 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 Rolling Moment Coefficient with Aileron Deflection 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 ]

Summary n 3 -View Drawing Launch Conditions Revisited Control Sizing Revisited Trim Diagram Control Derivatives n Questions? n n March 1, 2005 16 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

Appendix March 1, 2005 17 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

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 March 1, 2005 18 [ 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 Wortmann FX 63 -137: M. S. Selig, J. F. Donovan and D. B. Fraser, "AIRFOIL AT LOW SPEEDS – Wind Tunnel March 1, 2005 19 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 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 March 1, 2005 20 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

Airfoil Selection: Wing Wortmann FX 67 -137 Wortmann FX 63 -137: M. S. Selig, J. F. Donovan and D. B. Fraser, "AIRFOIL AT LOW SPEEDS – Wind Tunnel 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 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: 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 CLmax vs. Re 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: Canard NACA 0012 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 Abbott, I. H. & A. E. von Doenhoff, “Theory of Wing Sections” 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: Canard 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 ]

Geometry Wetted Area : 9. 013 ft 2 March 1, 2005 28 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

Airfoil Selection: Vertical Tails n Flat Plate ¡ ¡ Non-Lifting Surface No Volume Needed Ease of Construction Light Weight March 1, 2005 29 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

Mathematical Model No Wing Twist: Re=147, 820 March 1, 2005 30 [ 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 31 [ 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 32 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

Wing Twist Distribution n n Root: 1 o Tip: -7 o March 1, 2005 33 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

Mathematical Model n From Prandtl’s Classical Lifting-Line Theory 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 Re=147, 820 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 * Raymer, Daniel P. , Aircraft Design: A Conceptual Approach p. 493 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 March 1, 2005 37 [ Overview | 3 -View | Launch Conditions | Sizing 1 2 3 4 5 | Trim Diagram | Derivatives 1 2 3 4 5 ]

L/DMAX n n L/DMAX=10. 75 αL/Dmax=0. 60 o Re=147, 820 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 Velocity n Loiter Straight: ¡ n VL/Dmax= 21. 97 ft/s Loiter Turn: ¡ VL/Dmax= 23. 12 ft/s 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 ]

Endurance Assumptions n Level Flight n No Acceleration n Loiter~Straight Time = Loiter~Turning Time 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 ]