Objective
High intensity combustion is critical to high speed propulsion in ramjets and scramjets. A stable supersonic combustion is indispensable to maintain reasonble temperatures and pressures in the combustion chamber and to provide a useful combustion efficiency. To get more information about the combustion, the temperature and concentration distribution in the combustion chamber and their dependence on finite rates of combustion reactions must be investigated. The mixing process can be controlled by variation of shape and geometry of the hydrogen injector. Test runs will be performed at TsAGI and at DLR-Lampoldshausen. Nonintrusive optical diagnostic techniques like CARS will provide the temperature and concentration data. The experimental data must be compared with results of numerical calculations of this combustion. Here, the turbulence, chemical kinetics and pdf of temperature and species concentrations must be taken into account.
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74239 Hardthausen
Germany