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- W851898716 abstract "A series of experiments are reported using inclined circular wall jets in rectangular scramjet combustion chambers configured as constant area ducts. A free piston shock tunnel was used to create inlet flow Mach numbers between 4.2 and 5.5, at enthalpies corresponding to flight speeds of between 3.5 and 5.3 km/s. Measurements of duct static pressure levels indicated that significant mixing and combustion was achieved. Using hydrogen as a fuel, it was found that multipoint injection from two sides of the duct gave a larger, and more rapid, pressure rise. In hypersonic flow, it was found that combustion only occurred for the same duct dimensions and operating conditions that supported combustion with central injection from a two-dimensional strut. Wall injection from discrete orifice circular jets was found to be more effective than two-dimensional wall injection across the whole width of the duct." @default.
- W851898716 created "2016-06-24" @default.
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- W851898716 date "1991-01-01" @default.
- W851898716 modified "2023-09-24" @default.
- W851898716 title "Supersonic combustion with transverse, circular wall jets" @default.
- W851898716 hasPublicationYear "1991" @default.
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