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Consider air flow at standard sea level conditions over NACA 0010 airfoil. The maximum thickness of the airfoil is 4.2 cm, and the angle
Consider air flow at standard sea level conditions over NACA 0010 airfoil. The maximum thickness of the airfoil is 4.2 cm, and the angle of attack is 7.4 degrees. If the freestream velocity is 1 m/s calculate the magnitude of the circulation of the starting vortex?
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Answer We can use the KuttaJoukowski theorem to relate the circulation freestream velocity and airfo...
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Modern Compressible Flow With Historical
Authors: John Anderson
4th Edition
1260570827, 978-1260570823
