Questions from Fundamentals of Aerodynamics

Q: A supersonic flow at M1=3, T1=285 K

A supersonic flow at M1=3, T1=285 K, and p1=1 atm is deflected upward through a compression corner with θ=30.6◦ and then is subsequently expanded around a corner of the same angle such that the flow d...

Q: Consider an infinitely thin flat plate at an angle of attack α

Consider an infinitely thin flat plate at an angle of attack α in a Mach 2.6 flow. Calculate the lift and wave-drag coefficients for (a) α=5◦ (b) α=15◦ (c) α=30◦ (Note: Save the results of this prob...

Q: Consider a diamond-wedge airfoil such as shown in Figure 9

Consider a diamond-wedge airfoil such as shown in Figure 9.36, with a half-angle ε=10◦. The airfoil is at an angle of attack α=15◦ to a Mach 3 freestream. Calculate the lift and wave-drag coefficients...

Q: Consider the Space Shuttle during its atmospheric entry at the end of

Consider the Space Shuttle during its atmospheric entry at the end of a mission in space. At the altitude where the Shuttle has slowed to Mach 9, the local heat transfer at a given point on the lower...

Q: Consider sonic flow. Calculate the maximum deflection angle through which this

Consider sonic flow. Calculate the maximum deflection angle through which this flow can be expanded via a centered expansion wave.

Q: Consider a circular cylinder (oriented with its axis perpendicular to the

Consider a circular cylinder (oriented with its axis perpendicular to the flow) and a symmetric diamond-wedge airfoil with a half-angle of 5◦ at zero angle of attack; both bodies are in the same Mach...

Q: Consider the supersonic flow over a flat plate at an angle of

Consider the supersonic flow over a flat plate at an angle of attack, as sketched in Figure 9.35. As stated in Section 9.7, the flow direction downstream of the trailing edge of the plate, behind the...

Q: Consider a two-dimensional duct with a straight horizontal lower wall

Consider a two-dimensional duct with a straight horizontal lower wall, and a straight upper wall inclined upward through the angle θ=3◦. The height of the duct entrance is 0.3 m. A uniform horizontal...

Q: Repeat Problem 9.18, except with θ=30◦.

Repeat Problem 9.18, except with θ=30◦. Again, we will use these results to compare with a quasi-one-dimensional calculation in Problem 10.16. The reason for repeating this calculation is to examine t...

Q: Consider an oblique shock wave with a wave angle of 30◦

Consider an oblique shock wave with a wave angle of 30◦ in a Mach 4 flow. The upstream pressure and temperature are 2.65*104 N/m2 and 223.3 K, respectively (corresponding to a standard altitude of 10,...