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THE OBJECTIVE OF THE PROPOSED RESEARCH PROJECT IS THE DEVELOPMENT OF INNOVATIVE PHYSICAL MODELS AND ADVANCED HIGH ORDER NUMERICAL METHODS FOR THE RELIABLE PREDICTION OF AEROTHERMODYNAMIC FLOWS THAT ARE RELEVANT TO HYPERSONIC AND ATMOSPHERIC ENTRY VEHICLES. THIS RESEARCH ADDRESSES LIMITATIONS OF CURRENTLY EMPLOYED AEROTHERMODYNAMIC MODELING CAPABILITIES THAT LARGELY RELY ON TRADITIONAL LOWORDER FV FD FORMULATIONS. TO ENABLE THE ACCURATE SIMULATION OF PARTICLE LADEN REACTING FLOW ENVIRONMENTS A LAGRANGIAN PARTICLE METHOD WILL BE DEVELOPED. THIS METHOD CONSIDERS THE COUPLING BETWEEN TURBULENCE PARTICLE DISPERSION RADIATION PYROLYSIS AND NON EQUILIBRIUM CHEMISTRY AND THE EVOLUTION OF THE DISPERSE PHASE IS TWO WAY COUPLED WITH THE CARRIER PHASE TO ACCOUNT FOR EXCHANGE OF MOMENTUM ENERGY DEVOLATILIZATION AND PHASE TRANSITION. THE COMPLEMENTARY ALGORITHMIC RESEARCH EFFORT ADDRESSES THE CRITICAL EVALUATION OF HIGH ORDER DISCONTINUOUS GALERKIN DG METHODS FOR SIMULATING AEROTHERMODYNAMIC FLOWS AND HEAT TRANSFER ON UNSTRUCTURED AND NON CONFORMAL MESHES. FUNDAMENTAL ALGORITHMIC RESEARCH EFFORTS WILL FOCUS ON THE DEVELOPMENT OF A HP ADAPTATION METHOD AND A SHOCK CAPTURING TECHNIQUE THAT UTILIZE A RIGOROUS ENTROPY RESIDUAL FUNCTION. TO ACHIEVE OPTIMAL PERFORMANCE ON EMERGING HETEROGENEOUS AND MEMORY COMPLEX COMPUTE ARCHITECTURES WE EVALUATE THE POTENTIAL OF USING DOMAIN SPECIFIC PROGRAMMING PARADIGMS FOR ACCELERATING HIGH FIDELITY AEROTHERMODYNAMIC SIMULATIONS BY PERFORMING COMPUTE INTENSIVE KERNEL FUNCTIONS FOR CHEMISTRY INTEGRATION AND QUADRATURE EVALUATION ON HETEROGENEOUS COPROCESSORS. AN AMBITIOUS PERFORMANCE TARGET IS TO DEMONSTRATE EFFICIENCY IMPROVEMENTS OF THE RESULTING HIGH ORDER DG METHOD BY AT LEAST AN ORDER OF MAGNITUDE COMPARED TO STATE OF THE ART AEROTHERMODYNAMIC CODES AT COMPARABLE OR EVEN BETTER ACCURACY AND ROBUSTNESS. GROUND TEST EXPERIMENTS AND FLIGHT DATA WILL BE USED TO FACILITATE COMPREHENSIVE CODE VALIDATION AND CODE TO CODE COMPARISONS WITH CURRENT EDL SIMULATION CAPABILITIES SUCH AS LAURA FUN3D DPLR US3D WILL BE PERFORMED. THIS RESEARCH WILL LEVERAGE OUR EXPERTISE ON NUMERICAL METHODS ALGORITHMIC DEVELOPMENTS AND CHEMISTRY MODELING AND WILL FULLY UTILIZE OUR EXISTING MULTICOMPONENT REACTING DG SIMULATION CAPABILITY.

$823,445FY2015National Aeronautics and Space AdministrationNASA

The Leland Stanford Junior University

Investigators

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THE OBJECTIVE OF THE PROPOSED RESEARCH PROJECT IS THE DEVELOPMENT OF INNOVATIVE PHYSICAL MODELS AND ADVANCED HIGH ORDER NUMERICAL METHODS FOR THE RELIABLE PREDICTION OF AEROTHERMODYNAMIC FLOWS THAT ARE RELEVANT TO HYPERSONIC AND ATMOSPHERIC ENTRY VEHICLES. THIS RESEARCH ADDRESSES LIMITATIONS OF CURRENTLY EMPLOYED AEROTHERMODYNAMIC MODELING CAPABILITIES THAT LARGELY RELY ON TRADITIONAL LOWORDER FV FD FORMULATIONS. TO ENABLE THE ACCURATE SIMULATION OF PARTICLE LADEN REACTING FLOW ENVIRONMENTS A LAGRANGIAN PARTICLE METHOD WILL BE DEVELOPED. THIS METHOD CONSIDERS THE COUPLING BETWEEN TURBULENCE PARTICLE DISPERSION RADIATION PYROLYSIS AND NON EQUILIBRIUM CHEMISTRY AND THE EVOLUTION OF THE DISPERSE PHASE IS TWO WAY COUPLED WITH THE CARRIER PHASE TO ACCOUNT FOR EXCHANGE OF MOMENTUM ENERGY DEVOLATILIZATION AND PHASE TRANSITION. THE COMPLEMENTARY ALGORITHMIC RESEARCH EFFORT ADDRESSES THE CRITICAL EVALUATION OF HIGH ORDER DISCONTINUOUS GALERKIN DG METHODS FOR SIMULATING AEROTHERMODYNAMIC FLOWS AND HEAT TRANSFER ON UNSTRUCTURED AND NON CONFORMAL MESHES. FUNDAMENTAL ALGORITHMIC RESEARCH EFFORTS WILL FOCUS ON THE DEVELOPMENT OF A HP ADAPTATION METHOD AND A SHOCK CAPTURING TECHNIQUE THAT UTILIZE A RIGOROUS ENTROPY RESIDUAL FUNCTION. TO ACHIEVE OPTIMAL PERFORMANCE ON EMERGING HETEROGENEOUS AND MEMORY COMPLEX COMPUTE ARCHITECTURES WE EVALUATE THE POTENTIAL OF USING DOMAIN SPECIFIC PROGRAMMING PARADIGMS FOR ACCELERATING HIGH FIDELITY AEROTHERMODYNAMIC SIMULATIONS BY PERFORMING COMPUTE INTENSIVE KERNEL FUNCTIONS FOR CHEMISTRY INTEGRATION AND QUADRATURE EVALUATION ON HETEROGENEOUS COPROCESSORS. AN AMBITIOUS PERFORMANCE TARGET IS TO DEMONSTRATE EFFICIENCY IMPROVEMENTS OF THE RESULTING HIGH ORDER DG METHOD BY AT LEAST AN ORDER OF MAGNITUDE COMPARED TO STATE OF THE ART AEROTHERMODYNAMIC CODES AT COMPARABLE OR EVEN BETTER ACCURACY AND ROBUSTNESS. GROUND TEST EXPERIMENTS AND FLIGHT DATA WILL BE USED TO FACILITATE COMPREHENSIVE CODE VALIDATION AND CODE TO CODE COMPARISONS WITH CURRENT EDL SIMULATION CAPABILITIES SUCH AS LAURA FUN3D DPLR US3D WILL BE PERFORMED. THIS RESEARCH WILL LEVERAGE OUR EXPERTISE ON NUMERICAL METHODS ALGORITHMIC DEVELOPMENTS AND CHEMISTRY MODELING AND WILL FULLY UTILIZE OUR EXISTING MULTICOMPONENT REACTING DG SIMULATION CAPABILITY. · GrantIndex