Th e expansion section of a rocket nozzle is often conical in shape, and because the flow diverges, the thrust derived from the nozzle is less than it would be if the exit velocity were everywhere parallel to the nozzle axis. By considering the flow through the spherical section suspended by the cone and assuming that the exit pressure is equal to the atmospheric pressure, show that the thrust is given by

where m^· is the mass flow through the nozzle, V_e is the exit velocity, and α is the nozzle half-angle.

Transcribed Image Text:

(1 + cosa) T = mVe- 2