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Advanced Physics 9.5 A two-dimensional wedge-type diffuser of a military aircraft is flying at a Mach number of 2.5 and at an altitude where the ambient conditions are -56.5 C and 12 kPa is shown in Figure P9.5. The Mach number of the flow leaving the throat is 0.7; what is the value of the wedge angle 8,? For the shown two-dimensional supersonic inlet calculate the static and total temperatures and pressures at different states of the inlet. M. =2.5 Am = Ac