Aerodynamic Force Determination 2. Consider an infinitely thin flat plate with a 1 m chord at an angle of attack of 10°

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Aerodynamic Force Determination 2 Consider An Infinitely Thin Flat Plate With A 1 M Chord At An Angle Of Attack Of 10 1 (25.29 KiB) Viewed 29 times

Aerodynamic Force Determination 2. Consider an infinitely thin flat plate with a 1 m chord at an angle of attack of 10° in supersonic flow. The pressure and shear stress distributions on the upper and lower surfaces are given by P. = 4 x 10* (x - 1)2 +5.4 x 106, p. = 2 x 104 (x - 1)2 + 1.73 x 105, 1, = 288x02, and 1 = 731x02, respectively, where x is the leading edge in meters and p and t are in N/m². Calculate the normal and axial forces, the lift and drag, and moments about the leading edge.