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Aerodynamics QDR AAE451 – Team 3 October 9, 2003

Aerodynamics QDR AAE451 – Team 3 October 9, 2003. Brian Chesko Brian Hronchek Ted Light Doug Mousseau Brent Robbins Emil Tchilian. Airfoil Selection. Wing C L determined From constraint diagram (W/S) = 1.38 Dynamic pressure, q, for cruise conditions, and for near stall conditions.

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Aerodynamics QDR AAE451 – Team 3 October 9, 2003

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  1. Aerodynamics QDR AAE451 – Team 3 October 9, 2003 Brian Chesko Brian Hronchek Ted Light Doug Mousseau Brent Robbins Emil Tchilian

  2. Airfoil Selection • Wing CL determined • From constraint diagram (W/S) = 1.38 • Dynamic pressure, q, for cruise conditions, and for near stall conditions. • Rectangular wing geometry chosen for ease of construction, section lift coefficients found based on elliptical lift distribution. • Section Lift coefficients found at Cruise and Max lift conditions. • Examined different foils that would satisfy the above Cl at minimum drag.

  3. Airfoil Selection Rectangular Wing Cl distribution : Cruise: H = 1000ft V = 50ft/s Re = 93150 M = 0.0449 Elliptical Lift Distribution for minimum induced Drag

  4. Airfoil Selection • Based on the Cl variation (0-0.6), Xfoil was used to examine suitable foils.

  5. Airfoil Selection • Based on Drag Bucket location NACA 4412 was chosen.

  6. Airfoil Performance • NACA 4412, Cl generated for near stall Conditions H = Sl V = 33ft/s Re = 573540 M = 0.0269

  7. Airfoil Performance • NACA 4412 Foil, Rectangular planform, no taper, no sweep. • AR =5, Chord =2.8 ft, Span = 14 ft • CL = 1.29, CD = 0.025 (V=33 ft/s), CL = 0.481, CD = 0.015 (V=50ft/s) • S = 39 ft^2

  8. Questions?

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