Question

Refer to Figure 2.5 on page 105 of Aerodynamics for Naval Aviators. Calculate the velocity of the exhaust stream (V2) given the following information:
Ta = 12,000 lbs thrust
V1 = 1500 ft/s
Inlet Dia. = 3.43 ft
At standard sea level: Air Density (rho) = 2.377x10^-3 slugs/ft³
Q = Mass flow (slugs/s)

Calculate the velocity of the exit stream, V2.

A. 1895 ft/s

B. 1873 ft/s

C. 1864 ft/s

D. 1783 ft/s

Answer 1