Air having a reservoir pressure of 30 psia and density of 0.15 lb/ft is accelerated to a Mach number of 1.6. Find the static pressure, density, and temperature at this Mach number.
1. Air having a reservoir pressure of 30 psia and density of 0.15 lb/ft is accelerated to a Mach number of 1.6. Find the static pressure, density, and temperature at this Mach number.
2. Consider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are 5 atm and 500 K, respectively. If the Mach number at the nozzle exit is 3, calculate the exit pressure , temperature, and density. 4. A supersonic nozzle is a convergent-divergent duct , which is fed by a large reservoir at the inlet to the nozzle. In the reservoir of the nozzle, the pressure and temperature are 10atm and 550°R , respectively. At the nozzle exit, the pressure is 1 atm. Calculate the temperature and density of the flow at the exit. Assume the flow is isentropic and , of course, compressible.
3. The mass flow of air through a supersonic nozzle is 1.5 lbm/s. The exit velocity is 1,500 ft/sec, and the reservoir temperature and pressure are 1,000 'R and 7 atm , respectively. Calculate the area of the nozzle exit.
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