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- W2062614784 abstract "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." @default.
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- W2062614784 date "1989-07-12" @default.
- W2062614784 modified "2023-09-26" @default.
- W2062614784 title "Evaluation of parallel injector configurations for supersonic combustion" @default.
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- W2062614784 doi "https://doi.org/10.2514/6.1989-2525" @default.
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