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//All the quantities are expressed in SI units
p1 = 4.66e4; //ambient pressure
M = 8; //mach number
//from Appendix B, for M = 8
p0_2 = 82.87*p1; //total pressure downstream of the shock
//since the flow is isentropic downstream of the shock, total pressure is conserved
ps_atm = p0_2/101300; //pressure at the stagnation point
printf("\nRESULTS\n---------\nThe pressure at the nose is:\n p_s = %2.1f atm\n",ps_atm)
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