This paper presents a computational fluid dynamics (CFD) study of non-reacting and reacting flows in a scramjet model with three different throat heights. This scramjet model includes two compression ramps at the inlet, followed by a combustion chamber and thrust surfaces. The hydrogen is injected through an array of holes on the ramp surfaces, and the ignition is trigged by increased gas mixture temperature due to strong shock-shock interactions. The primary goal of the study is to evaluate the detailed shock-induced combustion processes by comparing CFD predictions with available experimental data, thus to understand the underlying combustion flow physics. For the ‘fuel off' cases, it was found that the CFD simulation produces the wall pressures in good agreement with the measurements. While for the ‘fuel on' cases, the CFD simulation results of combustion flow exhibit strong dependence on the turbulence model and turbulent combustion model choices. The desirable ‘radical farming' process has been only partially achieved in the flow field adjacent to the combustor walls, mainly due to the lacking of the penetration depth from the injector to the center main flow. The effect of fuel injection angle could affect the penetration depth and also the specific thrust of the scramjet engine.
Hyshot Scramjet
Two HyShot scramjet flights had previously been made—one on 30 October 2001 and another on 30 July 2002. Casino photography. Hq locksmith tallahassee. Supersonic combustion was achieved on the second flight. HyShot IV launch is planned for. The Hyshot scramjet engine is expected to push along a Terrior Orion rocket at Mach 7.6 - 7.6 times the speed of sound, or 2.4km a second - during a flight experiment at Woomera on August 13, with a repeat experiment with a second rocket on August 20. Slots youtube ng.
