Questions from Fundamentals of Aerodynamics

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...

Q: 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...

Q: Consider air at a temperature of 230 K. Calculate the speed

Consider air at a temperature of 230 K. Calculate the speed of sound.

Q: 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.

Q: 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?

Q: 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...

Q: 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