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Engineering, 27.10.2020 17:40, victor49
Assuming the inlet captures the entire flow at all flight Mach numbers, and the internal pressure is always high enough to stabilize a normal shock at the entrance of the internal duct, calculate and plot the stagnation pressure ratio across the combined shock system for the above flight Mach numbers.
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Engineering, 04.07.2019 08:10, doggo242
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Engineering, 04.07.2019 19:20, rida10309
At steady state, air at 200 kpa, 325 k, and mass flow rate of 0.5 kg/s enters an insulated duct having differing inlet and exit cross-sectional areas. the inlet cross-sectional area is 6 cm2. at the duct exit, the pressure of the air is 100 kpa and the velocity is 250 m/s. neglecting potential energy effects and modeling air as an 1.008 kj/kg k, determine ideal gas with constant cp = (a) the velocity of the air at the inlet, in m/s. (b) the temperature of the air at the exit, in k. (c) the exit cross-sectional area, in cm2
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Assuming the inlet captures the entire flow at all flight Mach numbers, and the internal pressure is...
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