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July 12, 2005, 02:59
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CFD v.s wind tunnel in airfoil
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I tried to compare CFD・s results with wind tunnel test in pressure coefficient(Cp) for a developed airplane with a symmetric airfoil . At trailing edge, CFD proved that uppersurface・s Cp and lowersurface・s Cp close to each other ; but, the results of wind tunnel test speaded apart each other. The wind tunnel test of F-16 ran the same conclusion.Why? Thought W/T only had finit pressureholes , the curves couldn・t diverge at trailing edge. According to Kutta condition, Cp curves of up/low surfaces at trailing edge must meet each other. Were W/T data incorrect ?
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