Frendi Research Corporation

Unique Award Key	CONT_AWD_NNX11CG77P_8000_-NONE-_-NONE-
Awarding Agency	National Aeronautics and Space Administration
Link	View Page

Description

Title	WE PROPOSE THE DEVELOPMENT OF A HIGH FIDELITY COMPUTATIONAL APPROACH FOR UNSTEADY CALCULATIONS OF STRONGLY SEPARATED NON-EQUILIBRIUM HIGH-ENTHALPY HYPERSONIC FLOWS. THE GOAL IS TO INTEGRATE THE NOW PROVEN PARTIALLY-AVERAGED NAVIER-STOKES (PANS) METHOD FOR UNSTEADY FLOW SIMULATIONS WITH THE MOST ADVANCED CLOSURE MODELS FOR COMPRESSIBILITY, HIGH-ENTHALPY (FLOW - THERMODYNAMICS COUPLING) AND NON-EQUILIBRIUM (FLOW - CHEMISTRY COUPLING) EFFECTS. THE PANS MODEL HAS BEEN ESTABLISHED AS A RELIABLE MODEL FOR COMPUTING SEPARATION IN LOW AND HIGH SPEED REGIMES IN TWO RECENTLY CONCLUDE NASA NRA PROJECTS -- 1. RANS AND PANS MODELING OF HYPERSONIC TURBULENT MIXING ENVIRONMENT; 2. MODELING OF STRONGLY SEPARATED FLOWS WITH THE PANS BRIDGING METHOD. THE CURRENT PROPOSAL IS TO INCORPORATE FURTHER HYPERSONIC EFFECT CLOSURES INTO PANS. PHYSICS-BASED CLOSURE MODELS FOR FLOW-THERMOCHEMISTRY INTERACTIONS HAVE BEEN UNDER DEVELOPMENT IN GIRIMAJI'S GROUP AT TEXAS A&M UNDER AFOSR MURI FUNDING -- TRANSITION AND TURBULENCE MODELING IN NON-THERMOCHEMICAL-EQUILIBRIUM HYPERSONIC FLOWS. IMPORTANT CLOSURE MODEL BUILDING BLOCKS FOR HYPERSONIC PROCESSES ARE NOW AVAILABLE FROM THE ABOVE FUNDAMENTAL RESEARCH EFFORTS. THE COMBINATION OF PANS AND THESE ADVANCED HIGH-SPEED MODELS WILL LEAD TO A UNIQUE CAPABILITY FOR COMPUTING HYPERSONIC FLOW SEPARATION WITH ABLATION, CHEMISTRY AND COMPRESSIBILITY EFFECTS. FOR PHASE I, WE PROPOSE A LOGICAL SEQUENCE OF VERIFICATION-VALIDATION COMPUTATIONS TO DEMONSTRATE THE POTENTIAL OF THE VARIOUS INDIVIDUAL CLOSURES IN SEPARATED HIGH-SPEED HIGH-ENTHALPY FLOWS. WHILE IN-HOUSE CODES ARE AVAILABLE FOR THE PROPOSED DEVELOPMENT, WE WILL ALSO CONSIDER USING ANY OF THE NASA CODES: USM3D, OVERFLOW, VULCAN OR ANY OF THE OTHER CODES SUGGESTED BY THE GRANTOR. SUBSEQUENT WORK (PHASE II) WILL FOCUS ON THE ASSEMBLY OF THE INDIVIDUAL COMPONENTS AND DEVELOPMENT OF AN UNIQUE HIGH-FIDELITY COMPUTATIONAL CAPABILITY FOR HYPERSONIC VEHICLE DESIGN, TESTING AND DEVELOPMENT.
NAICS Code	541712: RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY)
Product and Service Codes	AR11: R&D-AERO & SPACE TECH-B RES

Recipient Details

Recipient	FRENDI RESEARCH CORPORATION
UEI	Z4NSAJ88JQL6
Legacy DUNS	118538086
Recipient Address	UNITED STATES, 146 MANNINGHAM DR, MADISON, 357587418

Unique Award Key	CONT_AWD_NNX11CD05P_8000_-NONE-_-NONE-
Awarding Agency	National Aeronautics and Space Administration
Link	View Page

Description

Title	THE MAIN OBJECTIVE OF THIS RESEARCH EFFORT IS TO DEVELOP A HIGHER ORDER UNSTEADY TURBULENT FLOW SOLVER BASED ON THE FDV METHOD, AND TO EXPLOIT ITS ATTRIBUTES OF SPANNING THE WHOLE MACH NUMBER RANGE. THE WELL KNOWN ADVANTAGES OF THE IMPLICIT FEM WILL BE INHERITED ALONG WITH ROBUST BOUNDARY CONDITIONS IMPLEMENTATION AND SOUND MATHEMATICAL BASES. EFFICIENT PARALLELIZATION, USING MPI THROUGH DOMAIN DECOMPOSITION AND EBE SOLUTION, AND SUPPORTING UNSTRUCTURED GRIDS WILL MAKE THIS EFFORT A LONG-TERM INVESTMENT TOOL, SINCE ALL THESE GAINED ADVANTAGES ARE DESIRABLE IN VIRTUALLY EVERY NASA AERODYNAMICS APPLICATION. TO THIS END, MODULARIZATION OF THE IN-HOUSE DEVELOPED COMPUTER CODE WILL BE EXTENDED TO SUPPORT HIGHER ORDER ELEMENTS, NAMELY; QUADRATIC, CUBIC, AND EVENTUALLY SPECTRAL ELEMENTS. THE DEVELOPED HIGHER ORDER CODE WILL BE TESTED AT VARIOUS FLOW CONDITIONS STARTING FROM THE INCOMPRESSIBLE LIMIT TO HIGH SUPERSONICS, AND INCLUDING SUBSONICS AND TRANSONICS.
NAICS Code	541712: RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY)
Product and Service Codes	AR11: R&D-AERO & SPACE TECH-B RES

Recipient Details

Recipient	FRENDI RESEARCH CORPORATION
UEI	Z4NSAJ88JQL6
Legacy DUNS	118538086
Recipient Address	UNITED STATES, 7561 WALL TRIANA HWY, MADISON, 357578327