Secondary injection thrust vector control (SITVC) of a rocket motor, attitude control of a flight vehicle by side jet, and transverse fuel injection into a supersonic combustor have been studied. Two types of pressure probes were used, and wall static pressure was also measured. These measurements indicate that flow field downstream of the injection port was composed of some elementary parts which were discerned due to their physical features. The flow structure development downstream and the effect of the injection pressure on the flow structure together with the effect of secondary injection on the separation at the nozzle exit in the case of over-expanded main stream are also presented. (Author)
Secondary Gas Injection into a Supersonic Conical Nozzle
1976
40 pages
Report
Keine Angabe
Englisch
Secondary Gas Injection into a Supersonic Conical Nozzle
AIAA | 1977
|Secondary gas injection in conical rocket nozzle
Engineering Index Backfile | 1963
|SECONDARY GAS INJECTION IN A CONICAL ROCKET NOZZLE
AIAA | 1963
|