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clc
// Example 4.5.py
// Consider a 15 deg half angle wedge at zero angle of attack. Calculate the
// pressure coefficient on the wedge surface in a Mach 3 flow of air.
// Variable declaration
M1 = 3.0 // upstream mach number
theta = 15.0 // deflection (in degrees)
gamma1 = 1.4 // ratio of specific heats
// Calculations
// subscript 2 means behind the shock
// from figure 4.5 from M1 = 3.0, theta = 15.0 deg.
beta1 = 32.2 // shock angle (in degress)
// degree to radian conversion is done by multiplying by %pi/180
//
Mn1 = M1 * sin(beta1*%pi/180) // upstream mach number normal to the shock
// from Table A2 for Mn1 = 1.6
p2_by_p1 = 2.82 // p2/p1
Cp = 2/(gamma1*M1*M1) * (p2_by_p1 - 1)
// Results
printf("\n Coefficient of pressure is %.3f",(Cp))
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