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Consider a thin symmetric airfoil with 1.22 m chord in a uniform flow at V1 = 67 m/s and an angle of attack of 8

Consider a thin symmetric airfoil with 1.22 m chord in a uniform flow at V1 = 67 m/s and an angle of attack of 8 degrees. The free-stream pressure and density are 95760 N/m2 and 1.191 kg/m3 respectively

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