Accession Number : AD0758521

Title :   Vectored Thrust Control.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF

Personal Author(s) : Horais,Brian John

Report Date : DEC 1972

Pagination or Media Count : 99

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 the report. (Author)

Descriptors :   (*MOVABLE NOZZLES, *THRUST VECTOR CONTROL SYSTEMS), SUPERSONIC NOZZLES, NOZZLE GAS FLOW, SHOCK WAVES, NOZZLE AREA RATIO, VARIABLE AREA NOZZLES, FLOW FIELDS, FLOW VISUALIZATION, THESES

Subject Categories : Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE