At a given point in the high-speed flow over an airplane wing, the local Machnumber, static pressure, and static temperature are 0.7, 0.9 atm, and 250 K, respectively. Calculate the total pressure, total temperature at this point.

Refrigerant 134a enters an insulated compressor operating at steady state as saturated vapor at -26°c with a volumetric flow rate of 0.18 m3/s. refrigerant exits at 9 bar, 70°c. changes in kinetic and potential energy from inlet to exit can be ignored. determine the volumetric flow rate at the exit, in m3/s, and the compressor power, in kw.

During a steady flow process, the change of energy with respect to time is zero. a)- true b)- false

Carbon dioxide gas expands isotherm a turbine from 1 mpa, 500 k at 200 kpa. assuming the ideal gas model and neglecting the kinetic and potential energies, determine the change in entropy, heat transfer and work for each kilogram of co2.