edXproblem: 5.5.8 Supersonic flow past an upward ramp 5.1 5.3 Consider an upward ramp (concave corner) with angle = 10 as shown in the Figure below. The incoming airflow is supersonic with M = 1.5, P = 105 Pa, T = 298 K. Assume air behaves like an ideal gas with y=1.4 and R=287J/kg-K, and that the shock is weak. M2, P2, P2. T2 M, P, P, T 1) Determine the conditions past the shock. Use the B(0, M) chart below. B5 80 75 11 12 13 14 15 70 00 8 Ideal Provide the Mach number with three digits of precision (of the form X.YZeP): M = Provide the pressure (in Pascals) with three digits of precision (of the form X.YZeP): P2 = Provide the temperature with three digits of precision (of the form X.YZeP): T = Provide the density with two digits of precision (of the form X.YeP): p2 = [B] (weld 60 56 50 45 M-16 150