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Aerodynamic Airfoil Selection for Rectangular Wing Efficiency

This team project explores airfoil selection for a rectangular wing to enhance aerodynamic performance at cruise and near-stall conditions. Research involves Cl distribution analysis, drag minimization, and performance evaluation of NACA 4412 foils. The chosen foil shows improved lift coefficients and reduced drag, contributing to overall wing efficiency.

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Aerodynamic Airfoil Selection for Rectangular Wing Efficiency

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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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