THE CAPABILITY OF ACCURATELY SIMULATING SUPERSONIC COMBUSTION IS A VITAL TOPIC FOR DESIGNING AND ADVANCING HYPERSONIC AIR BREATHING VEHICLES. AS A CONSEQUENCE THERE IS HIGH DEMAND FOR ACCURATE VERSATILE AND COMPUTATIONALLY COST EFFECTIVE SUPERSONIC COMBUSTION MODELS. ADDITIONALLY THERE IS A LACK OF QUANTITATIVE COMPARATIVE STUDIES ON LARGE EDDY SIMULATION LES COMBUSTION MODELS. A RESEARCH INVESTIGATION TO CONDUCT A QUANTITATIVE COMPARATIVE STUDY OF PROMINENT LES TURBULENT COMBUSTION MODELS FOR SUPERSONIC COMBUSTION IS PROPOSED HEREIN. THE THREE TURBULENT COMBUSTION METHODOLOGIES THAT WILL BE INVESTIGATED ARE THE FLAMELET MODEL THE FILTERED MASS DENSITY FUNCTION FMDF MODEL AND THE LINEAR EDDY MIXING LEM MODEL. TO ASSESS THESE THREE METHODOLOGIES THREE VALIDATION EXPERIMENTS INVOLVING SUPERSONIC COMBUSTION WILL BE SIMULATED. THIS STUDY AIMS TO FIND THE ACCURACY VERSATILITY AND THE COMPUTATIONAL COST OF EACH OF THE INVESTIGATED LES COMBUSTION MODELS. FURTHERMORE THE DEFICIENCIES AND SHORTCOMINGS OF EACH OF THE MODELS WILL BE IDENTIFIED. THE OUTCOME OF THIS RESEARCH INVESTIGATION WILL DIRECTLY BENEFIT NASA'S LAUNCH PROPULSION SYSTEM RESEARCH OBJECTIVES. HIGH PRIORITY RESEARCH AREAS SUCH AS TURBINE BASED COMBINED CYCLE TBCC AND ROCKET BASED COMBINED CYCLE RBCC CAN BENEFIT FROM HIGH FIDELITY SIMULATION TOOLS.

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