Engineering, 26.09.2021 22:20, ariannawilder0210
The exhaust gases from a rocket engine can be assumed to behave as a perfect gas with a specific heat ratio of 1.3 and a molecular weight of 32. The gas is expanded from the combustion chamber through the nozzle. At a point in the nozzle where the cross-sectional area is 0.2 m2 , the pressure, temperature, and Mach number are 1500 kPa, 800°C, and 0.2, respectively. At some other point in the nozzle, the pressure is found to be 80 kPa. Find the Mach number, temperature, and crosssectional area at this point. Assume a one-dimensional, isentropic flow.
Answers: 2
Engineering, 03.07.2019 14:10, cowgyrlup124
Explain the difference laminar and turbulent flow. explain it with the shear stress and the velocity profiles.
Answers: 1
Engineering, 04.07.2019 18:10, oliviasoreo92
Compute the pressure drop of 30°c air flowing with a mean velocity of 8 m/s in a circular sheet-metal duct 300 mm in diameter and 15 m long. use a friction factor, f 0.02, and pair = 1.1644 kg/m a. 37.26 pa b. 25.27 pa n c. 29.34 pa d. 30.52 pa
Answers: 1
Engineering, 04.07.2019 18:20, Doogsterr
For each of the following process: a) sketch the p-v diagram, b)sketch t-s diagram, c) sketch t-v diagram, d) sketch the boundary work on one of the diagrams (a, b or c) and e) sketch the reversible heat transfer on one of the diagrams (a, b or c): 1- isobaric process from compressed liquid to superheated vapor 2- isothermal process from compressed liquid to superheated vapor 3- isentropic process from compressed liquid to superheated vapor
Answers: 3
The exhaust gases from a rocket engine can be assumed to behave as a perfect gas with a specific hea...
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