Engineering, 14.09.2019 01:30 drepeter86
Atmospheric air enters the intake diffuser of a jet aircraft flying at a mach number of 0.8 at a constant altitude where the static pressure and temperature are 25kpa and 220k, respectively. the entrance area of the intake is 0.5m2 and the area at entry to the compressor is 0.8 m2. there is a loss of 10% of the stagnation pressure of the air as it flows to the compressor. using compressible flow theory and assuming adiabatic flow in the intake, determine the mach number and velocity of the flow entering the compressor.
Answers: 1
Engineering, 04.07.2019 18:10
The temperature of air decreases as it is compressed by an adiabatic compressor. a)- true b)- false
Answers: 2
Engineering, 04.07.2019 18:10
Water at the rate of 1 kg/s is forced through a tube with a 2.5 cm inner diameter. the inlet water temperature is 15°c, and the outlet water temperature is 50°c. the tube wall temperature is 14°c higher than the local water temperature all along the length of the tube. what is the length of the tube?
Answers: 3
Engineering, 04.07.2019 18:10
Courses that are developed by subject matter experts, internal or extemal to the college or university. these programs are marketed by the school (clo2) marks a)-vocational schools b)-vendor training c)-colleges & universities d)-continuing education programs
Answers: 2
Engineering, 04.07.2019 18:20
Wiy doeres rere okhn a pump whon working betwon the same pressure range?
Answers: 2
Atmospheric air enters the intake diffuser of a jet aircraft flying at a mach number of 0.8 at a con...
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