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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) \ No newline at end of file