Read Experimental Studies of Flow Separation of the NACA 2412 Airfoil at Low Speeds - National Aeronautics and Space Administration | ePub Online

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Wind tunnel tests have been conducted on an NACA 2412 airfoil section at Reynolds number of 2.2 x 10(exp 6) and Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers have been obtained at angles of attack of 12.4 degrees, 14.4 degrees, and 16.4 degrees. Pre- and post-separated velocity and pressure survey results over the

Title : Experimental Studies of Flow Separation of the NACA 2412 Airfoil at Low Speeds
Author : National Aeronautics and Space Administration
Language : en
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Type : PDF, ePub, Kindle
Uploaded : Apr 11, 2021

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