Vectored thrust control.

Abstract

Supersonic two-dimensional flow from a nozzle with the exit plane inclined to the central axis of the nozzle will be turned if the exit pressure of the nozzle is not matched to the external pressure. The direction and magnitude of the flow deflection angle and the resulting deflection force is a function of the exit pressure of the nozzle, the exit Mach number and the amount the exit plane is inclined to the central axis of the nozzle. A study of the deflection forces and deflection angles generated for a Mach number range of 1.2 to 2.4 and for a wide range of exit pressures is presented in this paper.