Techniques for the enhancement of mixing in a scramjet combustor are presently investigated experimentally with wall-mounted parallel injector ramps that are speculated to prove useful at high speeds in the extraction of thrust from engine- or airframe-coolant hydrogen. The injector ramps were designed to generate a reflected shock wave from the duct top wall which will pass just downstream of the fuel injectors' barrel shock; fuel injector Mach number is 1.7, in virtue of which an underexpanded fuel flow is generated. Shadowgraph and UV-TV flow visualizations were conducted for three duct configurations.
Evaluation of parallel injector configurations for supersonic combustion
01.07.1989
Aufsatz (Konferenz)
Keine Angabe
Englisch
Ramp Injector Scale Effects on Supersonic Combustion
Online Contents | 2014
|Ramp Injector Scale Effects on Supersonic Combustion
AIAA | 2014
|