FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
6th Edition
ISBN: 9781265141387
Author: Anderson
Publisher: MCG
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Chapter 12, Problem 12.3P

Consider a diamond-wedge airfoil such as shown in Figure 9.26, with a half-angle ε = 1 0 ° . The airfoil is at an angle of attack α = 15 ° to a Mach 3 free stream. Using linear theory, calculate the lift and wave-drag coefficients for the airfoil. Compare these approximate results with those from the exact shock-expansion theory obtained in Problem 9.14.

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