Question Tag: airfoil
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How to calculate aerodynamics ?
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Consider an NACA 2412 airfoil with chord of 1.5 m at an angle of attack of 4°. For a free-stream …
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For a symmetric airfoil,the lift coefficient for zero degree angle of attack is
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The critical Mach number of an airfoil is attained when
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Stall in an aircraft occurs when there is a flow separation and reduction in the lift coefficient of the airfoil. …
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