Coupling of Computational Fluid Dynamics (CFD), Reentry Vehicle Surface Ablations, and In-Depth Conductions

Award Information
Agency:
Department of Defense
Branch:
Air Force
Amount:
$99,978.00
Award Year:
2005
Program:
SBIR
Phase:
Phase I
Contract:
FA8650-05-M-3530
Agency Tracking Number:
F051-241-0336
Solicitation Year:
2005
Solicitation Topic Code:
AF05-241
Solicitation Number:
2005.1
Small Business Information
COMBUSTION RESEARCH & FLOW TECHNOLOGY, I
6210 Keller's Church Road, Pipersville, PA, 18947
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
929950012
Principal Investigator
 Neeraj Sinha
 Vice President & Technical Director
 (215) 766-1520
 sinha@craft-tech.com
Business Contact
 Neeraj Sinha
Title: Vice President & Technical Director
Phone: (215) 766-1520
Email: sinha@craft-tech.com
Research Institution
N/A
Abstract
The innovation for this Phase I program is the extension of the new Rocket Plume Flowfield Model (RPFM) to analyze Reentry Vehicle (RV) body flows. The Phase I effort provides the foundation for a highly optimized, fast-running Reentry Vehicle Flowfield Model (RVFM) for analysis of thermal protection systems (TPS). Many of the key features are already in place to expedite RV flow solutions (GUI, NS/PNS flow solvers, self-contained automated grid generation and mesh adaptation, generalized thermo-chemistry, Expert Interface, etc.). Key extensions for Phase I would be the inclusion of body ablative routines and ablative heatshield thermo-chemistry data banks, as well as modification of the GUI and the self-contained grid/adaptive methodology to RV shock layer flows. Ablative modules that the authors had developed for the Air Force sponsored REACH code will be implemented and upgraded using high-fidelity surface transpiration boundary conditions. Overlaid procedures for charged species and fluctuating electron solutions developed for RPFM will be implemented to achieve fast run times. Phase I accomplishments will be demonstrated by simulating the descent trajectory of a representative RV from an altitude of ~300 kft to ground impact.

* information listed above is at the time of submission.

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