Validation of scramjet exhaust simulation technique, Volume 2688
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2-D MOC 2-D region 42 percent Argon 58 percent Freon Afterbody Pressure Distribution afterbody surface Argon and 58 boundary layer bow shock butions C.L. Pressure Dist cal/gm centerline pressure distribution combustion gas combustion products Combustion Runs Combustor Nozzle Exit computed Cp(T)dT detonation tube facility detonation tube simulator diaphragm Dimensional Region driven tube enthalpy Exit Plane Static gas blend Gas Impact Pressure gases heat transfer gauges ideal gas incident wave Long Side Plates Mach number Mach Number Distribution method of characteristics microns msec/cm Nozzle Exit Plane Oscilloscope Record percent Freon 13B1 Plane Static Pressure Planform View pres pressure measurements pressure transducers psia rH rH rH running conditions shock tube shock wave Short Side Plates shown in Fig Side Expansion Effects side wall expansion spectral radiance stagnation conditions stagnation point stagnation pressure stagnation temperature STEP AT NOZZLE substitute gas mixture Substitute Gas Results Substitute Gas Run thermodynamic tion total enthalpy tunnel