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+//All the quantities are expressedin SI units
+
+p1 = 2527.3; //ambient pressure at the altitude of 25 km
+T1 = 216.66; //ambient temperature at the altitude of 25 km
+p0_1 = 38800; //total pressure
+gam = 1.4; //ratio of specific heats
+R = 287; //universal gas constant
+pressure_ratio = p0_1/p1; //ratio of total to static pressure
+
+//for this value of pressure ratio, mach number is
+M1 = 3.4;
+
+//the speed of sound is given by
+a1 = sqrt(gam*R*T1)
+
+//thus the velocity can be calculated as
+V1 = M1*a1;
+
+printf("\nRESULTS\n---------\nThe Velocity of the airplane is:\n V1 = %4.0f m/s\n",V1) \ No newline at end of file