Questions from Fundamentals of Aerodynamics

Q: At a given point in a flow, T=700 ◦

At a given point in a flow, T=700 ◦R, p=1.6 atm, and V=2983 ft/s. At this point, calculate the corresponding values of p0, T0, p∗, T∗, and M∗.

Q: Consider the isentropic flow through a supersonic nozzle. If the test

Consider the isentropic flow through a supersonic nozzle. If the test-section conditions are given by p=1 atm, T=230 K, and M=2, calculate the reservoir pressure and temperature.

Q: Consider a flat plate at zero angle of attack in a hypersonic

Consider a flat plate at zero angle of attack in a hypersonic flow at Mach 10 at standard sea level conditions. At a point 0.5 m downstream from the leading edge, the local shear stress at the wall is...

Q: Consider the isentropic flow over an airfoil. The freestream conditions correspond

Consider the isentropic flow over an airfoil. The freestream conditions correspond to a standard altitude of 10,000 ft and M∞=0.82. At a given point on the airfoil, M=1.0. Calculate p and T at this po...

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=1 atm, T1=288 K, and M1=2.6. Calculate the following properties just downstream of the shock: p2, T2, ρ2, M2, p0,2, T0,2, and the change in...

Q: The pressure upstream of a normal shock wave is 1 atm.

The pressure upstream of a normal shock wave is 1 atm. The pressure and temperature downstream of the wave are 10.33 atm and 1390 ◦R, respectively. Calculate the Mach number and temperature upstream o...

Q: The entropy increase across a normal shock wave is 199.5

The entropy increase across a normal shock wave is 199.5 J/(kg. K). What is the upstream Mach number?

Q: A slender missile is flying at Mach 1.5 at low

A slender missile is flying at Mach 1.5 at low altitude. Assume the wave generated by the nose of the missile is a Mach wave. This wave intersects the ground 559 ft behind the nose. At what altitude i...

Q: Consider the supersonic flow over an expansion corner, such as given

Consider the supersonic flow over an expansion corner, such as given in Figure 9.25. The deflection angle θ=23.38◦. If the flow upstream of the corner is given by M1=2, p1=0.7 atm, T1=630◦R, calculate...

Q: A supersonic flow at M1=1.58 and p1=

A supersonic flow at M1=1.58 and p1=1 atm expands around a sharp corner. If the pressure downstream of the corner is 0.1306 atm, calculate the deflection angle of the corner.