This project has investigated the fundamental scaling laws for supersonic combustion in scramjets flying at Mach 8. Developing these laws is critical for successfully transitioning small-scale ground test and flight experiment data to the design of full-scale scramjet vehicles. To achieve this, the project has employed state-of-the-art diagnostics to investigate inlet- injection radical farming supersonic combustion in a shock tunnel over a wide range of dynamic pressures at flight Mach 8.
Combustion scaling laws and inlet starting for Mach 8 inlet-injection radical farming scramjets
2010
14 pages
Report
Keine Angabe
Englisch
Fluid Mechanics , Jet & Gas Turbine Engines , Jet engine inlets , Supersonic combustion ramjet engines , Hypersonic flight , Mach number , Fuel injection , Scaling factor , Computational fluid dynamics , Flight testing , Navier stokes equations , Hypersonics , Hypersonic test facilities , Combustion mechanisms , Supersonic combustion , Scramjet technology
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