Air fl ows adiabatically through a duct. At one section V1 =400 ft/s, T1 = 200 °F, and p1 = 35 lbf/in2 absolute, whilefarther downstream V2 = 1100 ft/s and p2 = 18 lbf/in2absolute. Compute (a) Ma2, (b) Umax, and (c) p02/p01.
Air fl ows adiabatically through a duct. At one section V1 =
400 ft/s, T1 = 200 °F, and p1 = 35 lbf/in2 absolute, while
farther downstream V2 = 1100 ft/s and p2 = 18 lbf/in2
absolute. Compute (a) Ma2, (b) Umax, and (c) p02/p01.
Understand that the stagnation temperature is constant during the flow through the duct as the flow is adiabatic.
Write the properties of air.
Write the expression for the stagnation temperature at the inlet to the duct and substitute the known values in the expression.
Write the expression for the stagnation temperature at the outlet to the duct and substitute the known values in the expression.
Write the expression for the Mach number at the outlet and substitute the known values in the above expression.
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