Consider an infinitely thin flat plate with a 1-m chord at an angle of attack of 10
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Consider an infinitely thin flat plate with a 1-m chord at an angle of attack of 10° in a supersonic flow. The pressure and shear stress distributions on the upper surfaces are given by pu = 4x 104(x- l)2 + 5.4 x 104, p1 = 2x 104(x- 1)2 + 1.73 x 105, τu = 288x –0.2, and τ1 = 731x–0.2, respectively, where x is the distance from the leading edge in meters and p and τ are in Newton’s per square meter. Calculate the normal and axial forces, the lift and drag, moments about the leading edge, and moments about the quarter chord, all per unit span. Also, calculate the location of the center of pressure.
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For a flat plate e 0 in Eqs 17 111 Hence C 1 f N PP dx S 0 A N 210 E xx 119 10 x 2 N C 0 T T dx ...View the full answer
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