-8D Static Free-stream pressure pressure Ps Stagnation pressure 4 to 8 holes +10% Static pressure Po Ps Stagnation pressure -10% 0° Differential 10° 20 Yaw angle 0 pressure transducer JO.Lg

A normal shock occurs in a stream of oxygen. The oxygen flows at Ma=1.8 and the upstream pressure and temperature are 40 psia and 85 degrees Fahrenheit. a) Calculate the following on the downstream side of the shock: static pressure, stagnation pressure, static temperature, stagnation temperature, static density, and velocity. b)If the Mach number is doubled to 3.6, what will be the resulting values of the parameters listed in part (a)?

Consider steady, isentropic flow of air through a duct with varying area. At section 1, p1 = 60.0 kPa (abs), T1 = 27°C, Vị = 486 m/s. At a downstream section 2, p2 = 78.8 kPa (abs). Determine: a. Mach number, Maz b. sketch geometry of the duct

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