Team 5 Aerodynamics PDR Presented By Christian Naylor

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

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

Airfoil Sections – Wing n Wing ¨ Eppler n E 212 Tail ¨ Eppler E 169 Horizontal Tail ¨ NACA 0010 Vertical Tail February 17, 2005 AAE 451 – Team 5 3

Geometry – Wing n Sizing ¨ Weight : 0. 6 lbs ¨ W/S: 0. 38 lbs/ft 2 ¨ Wing Area: 1. 58 ft 2 n Geometry Simplification ¨ 2 Trapezoid Sections February 17, 2005 AAE 451 – Team 5 4

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

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

Geometry – Tail n Define Tail Volume Coefficients based on similar aircraft: ¨ Cvt = 0. 04 ¨ Cht = 0. 50 n Find tail areas ¨ Svt=cvtb. S/Lvt = 0. 20 sq ft ¨ Sht=chtc. S/Lht = 0. 47 sq ft February 17, 2005 AAE 451 – Team 5 7

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

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

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

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

Mathematical Model – Lift Curve Lift Coefficients vs. α CL CL and Cl Spanwise Lift Coefficient Distribution Span (ft) α (deg) Max Lift at Cruise α: 0. 74 lbf February 17, 2005 CLmax (Hembold): 0. 74 Max Lift (Hembold): 1. 10 lbf AAE 451 – Team 5 12

Mathematical Model – Drag Calculated from Lifting Line Theory 1 n e=0. 75 Drag Polar CD n CL 1 Anderson, J. D. , Fundamentals of Aerodynamics, New York, 2001, pp 351 -416 February 17, 2005 AAE 451 – Team 5 13

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

Mathematical Model – L/Dmax=11. 89 n Cruise at α=3° L/D vs. α L/D n α (deg) February 17, 2005 AAE 451 – Team 5 15

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

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

Control Surfaces n Sizes ¨ Aileron Area: 0. 082 ft 2 (each) ¨ Elevator Area: 0. 176 ft 2 ¨ Rudder Area: 0. 039 ft 2 (each) February 17, 2005 AAE 451 – Team 5 18

Endurance February 17, 2005 § Battery Wgt. Fraction = 0. 064 § Battery Weight = 0. 038 lbs. AAE 451 – Team 5 19

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