At a given point on the airfoil surface with very low speeds, the pressure coefficient is 0.3.

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At a given point on the airfoil surface with very low speeds, the pressure coefficient is 0.3. If the Mach number of the free stream is 0.6, then CP calculated at this point is?

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Aerodynamics

ISBN: 9789811945861

1st Edition

Authors: Peiqing Liu

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Question Posted: Apr 29, 2024 06:01 AM

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At a given point on the airfoil surface with very low speeds, the pressure coefficient is 0.3.

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The pressure coefficient CP can be calculated using the following formula ...View the full answer

Aerodynamics

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