Plot the pressure and temperature in the region adjacent to the upper surface as functions of angle of attack, α, ranging from α 5 0to 30.

An airfoil has a sharp leading edge with an included

angle of δ 5 60. It is being tested in a wind tunnel running at

1200 m/s (the air pressure and temperature upstream are 75

kPa and 3.5C). Plot the pressure and temperature in the

region adjacent to the upper surface as functions of angle of

attack, α, ranging from α 5 0to 30. What are the maximum

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Determine the thrust available to propel the cart.

A CO2 cartridge is used to propel a small rocket cart. Compressed gas, stored at 35 MPa and 20C, is expanded through a smoothly contoured converging nozzle with 0.5 mm….

Determine the range(s) of inlet stagnation pressures for which the nozzle will be free from normal shocks.

A converging-diverging nozzle, with Ae/At 5 1.633, is designed to operate with atmospheric pressure at the exit plane. Determine the range(s) of inlet stagnation pressures for which the nozzle will….

Find the range of exit pressures for which the duct exit flow is choked.

Room air is drawn into an insulated duct of constant area through a smoothly contoured converging nozzle. Room conditions are T 5 80 F and p 5 14:7 psia. The….