Q: In the reservoir of a supersonic wind tunnel, the velocity is
In the reservoir of a supersonic wind tunnel, the velocity is negligible, and the temperature is 1000 K. The temperature at the nozzle exit is 600 K. Assuming adiabatic flow through the nozzle, calcul...
See AnswerQ: An airfoil is in a freestream where p∞ = 0.
An airfoil is in a freestream where p∞ = 0.61 atm, ρ∞ = 0.819 kg/m3, and V∞=300 m/s. At a point on the airfoil surface, the pressure is 0.5 atm. Assuming isentropic flow, calculate the velocity at tha...
See AnswerQ: Consider air at a temperature of 230 K. Calculate the speed
Consider air at a temperature of 230 K. Calculate the speed of sound.
See AnswerQ: The flow just upstream of a normal shock wave is given by
The flow just upstream of a normal shock wave is given by p1=1800 lb/ft2, T1=480 ◦R, and M1=3.1. Calculate the velocity and M∗ behind the shock.
See AnswerQ: Consider a flow with a pressure and temperature of 1 atm and
Consider a flow with a pressure and temperature of 1 atm and 288 K. A Pitot tube is inserted into this flow and measures a pressure of 1.555 atm. What is the velocity of the flow?
See AnswerQ: Consider a flow with a pressure and temperature of 2116 lb/
Consider a flow with a pressure and temperature of 2116 lb/ft2 and 519 ◦R, respectively. A Pitot tube is inserted into this flow and measures a pressure of 7712.8 lb/ft2. What is the velocity of this...
See AnswerQ: Repeat Problems 8.11 and 8.12 using (incorrectly
Repeat Problems 8.11 and 8.12 using (incorrectly) Bernoulli’s equation for incompressible flow. Calculate the percent error induced by using Bernoulli’s equation
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