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+clc
+// Example 4.6.py
+// Consider a 15 deg half angle wedge at zero angle of attack in a Mach 3 flow of
+// air. Calculate the drag coefficient. Assume that the pressure exerted over the 
+// base of the wedge, the base pressure, is equal to the free stream pressure.
+
+
+
+// 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
+
+cd1 = 4/(gamma1*M1*M1)*(p2_by_p1 - 1)*tan(theta*%pi/180)
+
+
+// Results
+printf("\n Coefficient of drag is %.3f",(cd1))
+