Numerical Investigation of Turbulent Reacting Flows in a Scramjet Combustor Model

For the design of airbreathing hypersonic vehicles the simulation of the flow inside the propulsion system is of essential interest. Due to the importance of supersonic combustion in airbreathing hypersonic propulsion the flowfield within a scramjet combustor model has been investigated numerically. In the model hydrogen was injected through a symmetric wedge parallel into a heated Mach 2.0 air stream. The simulated test conditions correspond to a free flight Mach number up to Ma=5.5.