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Unified Kinetic/Continuum Flow Solver with Adaptive Cartesian Mesh for Hypersonic Flows in the Earth Atmosphere

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9550-09-C-0104
Agency Tracking Number: F08A-019-0071
Amount: $99,963.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: AF08-T019
Solicitation Number: 2008.A
Timeline
Solicitation Year: 2008
Award Year: 2009
Award Start Date (Proposal Award Date): 2008-09-01
Award End Date (Contract End Date): 2009-05-01
Small Business Information
215 Wynn Dr., 5th Floor
Huntsville, AL 35805
United States
DUNS: 185169620
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: No
Principal Investigator
 Vladimir Kolobov
 Manager, Plasma Technology
 (256) 726-4800
 tsb@cfdrc.com
Business Contact
 Deb Phipps
Title: Contracts Specialist
Phone: (256) 726-4884
Email: dap@cfdrc.com
Research Institution
 GEORGIA TECH RESEARCH CORP.
 R. P Hart III
 
Georgia Institute of Technolog 505 Tenth Street NW
Atlanta, GA 30332
United States

 (404) 894-6929
 Nonprofit College or University
Abstract

The design of future hypersonic vehicles requires detailed understanding of flow regimes ranging from rarefied to continuum. Moreover, hypervelocity flows are characterized by high temperatures, excitation of vibrational level of molecules, nonequilibrium dissociation, and ionization. The goal of this project is to develop unified kinetic/continuum solution methods with proper domain decomposition for a wide range of Air Force Applications. The Unified Flow Solver (UFS) with Adaptive Mesh and Algorithm Refinement, developed by CFDRC, will be enhanced by the advanced capabilities of the NASCART-GT viscous flow solver from Georgia Tech, and demonstrated for viscous/inviscid problems covering rarefied and continuum flow regimes. The octree based Cartesian mesh methods will be improved to better resolve viscous boundary layers and heat transfer simulations near surfaces. Phase I work will demonstrate the feasibility of kinetic/continuum algorithms with Cartesian mesh to compute heat transfer for dissociating and ionizing hypersonic flows. During Phase II, the advanced numerical techniques will be incorporated into a user-friendly code, and a general-purpose chemistry module and turbulence models will be added to the continuum solvers. The code will be validated for heat transfer simulations with Cartesian mesh and demonstrated for several benchmark cases including heat transfer prediction on a Mach 16 flow over bi-conic body.

* Information listed above is at the time of submission. *

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