Questions from Fundamentals of Aerodynamics

Q: Consider a Mach 3 flow at 1 atm pressure initially moving over

Consider a Mach 3 flow at 1 atm pressure initially moving over a flat horizontal surface. The flow then encounters a 20 degree expansion corner, followed by a 20 degree compression corner that turns t...

Q: The purpose of this problem is to explain what causes the dramatic

The purpose of this problem is to explain what causes the dramatic white cloud pattern generated in the flow field over the F/A-18C Hornet shown on the cover of this book. This problem is both a tutor...

Q: Equation (8.80) does not hold for an oblique

Equation (8.80) does not hold for an oblique shock wave, and hence the column in Appendix B labeled p0,2/ p1 cannot be used, in conjunction with the normal component of the upstream Mach number, to ob...

Q: Consider an oblique shock wave with a wave angle of 36.

Consider an oblique shock wave with a wave angle of 36.87◦. The upstream flow is given by M1=3 and p1=1 atm. Calculate the total pressure behind the shock using a. p0,2/ p0,1 from Appendix B (the corr...

Q: The purpose of this problem is to give you a feel for

The purpose of this problem is to give you a feel for the magnitude of Reynolds number appropriate to real airplanes in actual flight. a. Consider the DC-3 shown in Figure 1.1. The wing root chord len...

Q: Consider the flow over a 22.2◦ half-angle

Consider the flow over a 22.2◦ half-angle wedge. If M1 = 2.5, p1 = 1 atm, and T1 = 300 K, calculate the wave angle and p2, T2, and M2.

Q: Consider a flat plate at an angle of attack α to a

Consider a flat plate at an angle of attack α to a Mach 2.4 airflow at 1 atm pressure. What is the maximum pressure that can occur on the plate surface and still have an attached shock wave at the lea...

Q: A 30.2◦ half-angle wedge is inserted into

A 30.2◦ half-angle wedge is inserted into a freestream with M∞ = 3.5 and p∞=0.5 atm. A Pitot tube is located above the wedge surface and behind the shock wave. Calculate the magnitude of the pressure...

Q: Consider a Mach 4 airflow at a pressure of 1 atm.

Consider a Mach 4 airflow at a pressure of 1 atm. We wish to slow this flow to subsonic speed through a system of shock waves with as small a loss in total pressure as possible. Compare the loss in to...

Q: Consider an oblique shock generated at a compression corner with a deflection

Consider an oblique shock generated at a compression corner with a deflection angle θ=18.2◦. A straight horizontal wall is present above the corner, as shown in Figure 9.19. If the upstream flow has t...