Supersonic Flow over a wedge and cone M-3 Air flowing with a Mach number of 3,...

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Supersonic Flow over a wedge and cone M₁-3 Air flowing with a Mach number of 3, a pressure of 1 atm and a temperature of 300K passed over a 15° angle wedge leads to the generation of an oblique shock wave. ● 15° 1. Determine Mach number behind the shock M₂ and pressure coefficient Cp Where ● Shock wave angle ß can be found from deflection angle 0. Upstream Mach number perpendicular to the shock (Mn1): Mn1 = M₁ sin ß. Mach number behind the shock can be found from M₂ = M₁2/ sin (ß-0) Pressure Coefficient (Cp) can be found from: C₂=(2 y¹ M₁2)(p2/p₁ - 1), Supersonic Flow over a wedge and cone M₁-3 Air flowing with a Mach number of 3, a pressure of 1 atm and a temperature of 300K passed over a 15° angle wedge leads to the generation of an oblique shock wave. ● 15° 1. Determine Mach number behind the shock M₂ and pressure coefficient Cp Where ● Shock wave angle ß can be found from deflection angle 0. Upstream Mach number perpendicular to the shock (Mn1): Mn1 = M₁ sin ß. Mach number behind the shock can be found from M₂ = M₁2/ sin (ß-0) Pressure Coefficient (Cp) can be found from: C₂=(2 y¹ M₁2)(p2/p₁ - 1),

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In the problem provided you are asked to determine the Mach number behind an oblique shock wave M2 and the pressure coefficient Cp when air at a Mach ... View the full answer