In low-speed incompressible flow, the peak pressure coefficient (at the minimum pressure point) on an NACA 0012

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In low-speed incompressible flow, the peak pressure coefficient (at the minimum pressure point) on an NACA 0012 airfoil is —0.41. Estimate the critical Mach number for this airfoil, using the Prandtl-Glauert rule.

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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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In low-speed incompressible flow, the peak pressure coefficient (at the minimum pressure point) on an NACA 0012

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Fundamentals of Aerodynamics

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