FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
6th Edition
ISBN: 9781265141387
Author: Anderson
Publisher: MCG
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Chapter 5, Problem 5.10P
If the elliptical wing of the Spitfire in Problem 5.9 were replaced by a tapered wing with a taper ratio of 0.4, everything else remaining the same, calculate the induced drag coefficient. Compare this value with that obtained in Problem 5.9. What can you conclude about the relative effect of planform shape change on the drag of the airplane at high speeds?
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For a 10 deg included angle wedge at 0 deg AOA, calculate the lift and drag coefficient (Cl = 0, Cd = 0.082). Then calculate the lift and drag at AOA=4 deg (Cl = 0.16, Cd = 0.093).
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6. For a wing of aspect ratio AR, having an elliptical lift distribution, the induced drag coefficient is
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(c) Dimensionless
Chapter 5 Solutions
FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
Ch. 5 - Consider a vortex filament of strength in the...Ch. 5 - Consider the same vortex filament as in Problem...Ch. 5 - The measured lift slope for the NACA 23012 airfoil...Ch. 5 - The Piper Cherokee (a light, single-engine general...Ch. 5 - Consider the airplane and flight conditions given...Ch. 5 - Consider a finite wing with an aspect ratio of 6....Ch. 5 - Repeat Problem 5.6, except for a lower aspect...Ch. 5 - In Problem 1.19 we noted that the Wright brothers,...Ch. 5 - Consider the Superrnarine Spitfire shown in Figure...Ch. 5 - If the elliptical wing of the Spitfire in Problem...
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