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
1989-07-01
Conference paper
No indication
English
Ramp Injector Scale Effects on Supersonic Combustion
Online Contents | 2014
|Ramp Injector Scale Effects on Supersonic Combustion
AIAA | 2014
|