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

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Overview 3-View Drawing Launch Conditions Revisited Control Sizing Revisited Trim Diagram Control Derivatives

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Mission Requirements 15 min. endurance Take-off distance ≤ 60 ft. V stall ≤ 15 ft/s V loiter ≤ 25 ft/s 35 ft. turn radius Aircraft 3-View

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Launch Conditions Revisited α Lo = -9 o V take-off = 1.2V stall = 18 ft/s Climb Angle = 20 o Angle of Attack = 4.5 o -9 o 20 o 4.5 o

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, X-Plot Revisited

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Sizing Revisited Class 1 Sizing Class 2 Sizing Canard Area S ht 1.43 ft ft 2 Vertical Tail Area S vt (each) 0.92 ft ft 2

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Sizing Revisited Span (ft)Chord (ft)Area (ft 2 ) Aileron (each) Elevator Rudder (each)

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Effect of Control Surface Deflection: Lift Roskam,Jan, Airplane Design PartVI: Prelimenary Calculation of Aerodynamic, Thrust, and Power Characteristics, 2000

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Effect of Control Surface Deflection: Pitching Moment Roskam,Jan, Airplane Design PartVI: Prelimenary Calculation of Aerodynamic, Thrust, and Power Characteristics, 2000

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Trim Diagram C L Max Trimmed Maximum C L (x ref = x cg ) α CL Max α = 0 o

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Variation of Yawing Moment Coefficient with Sideslip Angle Roskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Variation of Rolling Moment Coefficient with Sideslip Angle Roskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Variation of Pitching Moment Coefficient with Elevator Angle Roskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Variation of Yawing Moment Coefficient with Rudder Deflection Roskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Variation of Rolling Moment Coefficient with Aileron Deflection Roskam,Jan, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes, 1977

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Summary 3-View Drawing Launch Conditions Revisited Control Sizing Revisited Trim Diagram Control Derivatives Questions?

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Appendix

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, 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

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, WORTMANN FX Wortmann FX : M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel Airfoil Selection: Wing

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, 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 : M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel Airfoil Selection: Wing

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Airfoil Selection: Wing Wortmann FX Wortmann FX : M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Airfoil Selection: Wing Wortmann FX : M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Airfoil Selection: Wing Wortmann FX : M.S.Selig,J.F.Donovan and D.B.Fraser,"AIRFOIL AT LOW SPEEDS – Wind Tunnel

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Airfoil Selection: Wing C Lmax vs. Re

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Airfoil Selection: Canard NACA 0012

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Airfoil Selection: Canard Abbott, I.H. & A.E. von Doenhoff, “Theory of Wing Sections”

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Airfoil Selection: Canard Abbott, I.H. & A.E. von Doenhoff, “Theory of Wing Sections”

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Geometry Wetted Area : ft 2

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Airfoil Selection: Vertical Tails Flat Plate  Non-Lifting Surface  No Volume Needed  Ease of Construction  Light Weight

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Mathematical Model No Wing Twist: Re=147,820

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Wing Twist Distribution

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Wing Twist Distribution *Neglecting Parasite Drag *

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Wing Twist Distribution Root: 1 o Tip: -7 o

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Mathematical Model From Prandtl’s Classical Lifting-Line Theory

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Mathematical Model Re=147,820

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Mathematical Model * Raymer, Daniel P., Aircraft Design: A Conceptual Approach p.493

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Mathematical Model

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, L/D MAX L/D MAX =10.75 α L/Dmax =0.60 o Re=147,820

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, L/D MAX L/D MAX Velocity Loiter Straight:  V L/Dmax = ft/s Loiter Turn:  V L/Dmax = ft/s Re=147,820

[ Overview | 3-View | Launch Conditions | Sizing | Trim Diagram | Derivatives ]Overview3-View Launch Conditions12345Trim Diagram12345 March 1, Endurance Re=147,820 Assumptions Level Flight No Acceleration Loiter~Straight Time = Loiter~Turning Time