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Team “Canard” September 19th, 2006. Aerodynamics 2 PDR. Overview. Aircraft Geometry: - Airfoil selection for wing and tail - Wing and tail configuration - Aspect ratio and wetted area - 3-View drawing Aerodynamic Mathematical Model: - C L - C D - C M. Wing and Tail Geometry.
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Team “Canard” September 19th, 2006 Aerodynamics 2 PDR
Overview Aircraft Geometry: - Airfoil selection for wing and tail - Wing and tail configuration - Aspect ratio and wetted area - 3-View drawing Aerodynamic Mathematical Model: - CL - CD - CM AAE 451 Team 1
Wing and Tail Geometry Maximum velocity : 115 ft/s Aircraft wetted area : 12.21 ft2 AAE 451 Team 1
3-View Drawing AAE 451 Team 1
Mathematical Model Lift Coefficient 3D: (From Flight Stability and Automatic Control, Robert C. Nelson) η: Dynamic pressure ratio αw: Angle of attack for the wing αt: Angle of attack for the tail St/S: Horizontal Tail area/Wing area ratio δe: Elevator deflection angle CL: Total Lift Coefficient CLo: CL at α = 0 CL,αw: Lift coeff. slope for wing CL,αt: Lift coeff. slope for tail CL,δe: Lift coeff. slope due to δe AAE 451 Team 1
Wing Lift Coefficient Less than 2π AAE 451 Team 1
CL Plot for Wing Blue Line: XFOIL Red Line: 3D AAE 451 Team 1
Tail Lift Coefficient 0 AAE 451 Team 1
CL Plot for Tail Blue Line: XFOIL Red Line: 3D AAE 451 Team 1
Elevator Effect on CL (From Flight Stability and Automatic Control, Robert C. Nelson) AAE 451 Team 1
Maximum Lift Coefficient CLMax from Lift Curve Needed CLMax Needed ΔCLMax: 0.32 AAE 451 Team 1
Mathematical Model Drag Coefficient Small due to Swet AAE 451 Team 1
Drag Polar Blue Line: XFOIL Red Line: 3D AAE 451 Team 1
Mathematical Model Moment Coefficient 3D: (From Flight Stability and Automatic Control, Robert C. Nelson) Cm,δe : Change of Cm due to δe αw: Angle of attack for the wing δe: Elevator deflection angle Cm : Total Moment Coefficient Cmo : Cm at α = 0 Cm,αw : Change of Cm due to αw AAE 451 Team 1
0 lt ac ac cg 25% 33% Zero Moment Coefficient AAE 451 Team 1
Moment Coefficient AAE 451 Team 1
Moment Coefficient AAE 451 Team 1
Questions Any Questions? AAE 451 Team 1