Consider the isentropic flow over an airfoil. The free stream conditions are T = 245 K and

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Consider the isentropic flow over an airfoil. The free stream conditions are T∞ = 245 K and p∞ = 4.35x 104 N/m2. At a point on the airfoil, the pressure is 3.6 x 104 N/m2. Calculate the density at this point.

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Fundamentals of Aerodynamics

ISBN: 978-0070016798

2nd Edition

Authors: J. Anderson

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Question Posted: Dec 09, 2010 03:24 AM

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Consider the isentropic flow over an airfoil. The free stream conditions are T = 245 K and

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Fundamentals of Aerodynamics

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