Questions from Fundamentals of Aerodynamics

Q: Repeat Problem 9.13 using a. Newtonian theory

Repeat Problem 9.13 using a. Newtonian theory b. Modified newtonian theory Compare these results with those obtained from exact shock-expansion theory (Problem 9.13). From this comparison, what commen...

Q: Consider a flat plate at α=20◦ in a Mach

Consider a flat plate at α=20◦ in a Mach 20 freestream. Using straight newtonian theory, calculate the lift- and wave-drag coefficients. Compare these results with exact shock-expansion theory.

Q: Consider a hypersonic vehicle with a spherical nose flying at Mach 20

Consider a hypersonic vehicle with a spherical nose flying at Mach 20 at a standard altitude of 150,000 ft, where the ambient temperature and pressure are 500◦R and 3.06 lb/ft2, respectively. At the p...

Q: Consider the incompressible viscous flow of air between two infinitely long parallel

Consider the incompressible viscous flow of air between two infinitely long parallel plates separated by a distance h. The bottom plate is stationary, and the top plate is moving at the constant veloc...

Q: Assume that the two parallel plates in Problem 15.1 are

Assume that the two parallel plates in Problem 15.1 are both stationary but that a constant pressure gradient exists in the flow direction (i.e., dp/dx = constant). a. Obtain an expression for the var...

Q: The wing on a Piper Cherokee general aviation aircraft is rectangular,

The wing on a Piper Cherokee general aviation aircraft is rectangular, with a span of 9.75 m and a chord of 1.6 m. The aircraft is flying at cruising speed (141 mi/h) at sea level. Assume that the ski...

Q: For the case in Problem 19.1, calculate the boundary

For the case in Problem 19.1, calculate the boundary-layer thickness at the trailing edge for a. Completely laminar flow b. Completely turbulent flow

Q: For the case in Problem 19.1, calculate the skin

For the case in Problem 19.1, calculate the skin-friction drag accounting for transition. Assume the transition Reynolds number = 5 × 105.

Q: Consider Mach 4 flow at standard sea level conditions over a flat

Consider Mach 4 flow at standard sea level conditions over a flat plate of chord 5 in. Assuming all laminar flow and adiabatic wall conditions, calculate the skin-friction drag on the plate per unit s...

Q: Consider a length of pipe bent into a U-shape.

Consider a length of pipe bent into a U-shape. The inside diameter of the pipe is 0.5 m. Air enters one leg of the pipe at a mean velocity of 100 m/s and exits the other leg at the same magnitude of v...