In: Mechanical Engineering
A jet engine flies at 205 m/s at an altitude where the
pressure is 0.466atm and...
A jet engine flies at 205 m/s at an altitude where the
pressure is 0.466atm and the temp is 249K. The pressure recovery
factor across the intake is 1.0 and the compressor pressure ratio
is 30. Assume isentropic turbomachinery.
A) determine flight mach number
B) determine stagnation pressure and temp at the inlet of the
intake
C) determine the stagnation pressure and temp after the
compeessor
D) determine the stagnation temp change across the turbine
drivibg the compressor