Base Flow Model Validation

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNM06AB12C
Agency Tracking Number: 040073
Amount: $599,987.00
Phase: Phase II
Program: STTR
Awards Year: 2006
Solicitation Year: 2004
Solicitation Topic Code: T8.02
Solicitation Number: N/A
Small Business Information
Combustion Research and Flow Technology
6210 Kellers Church Road, Pipersville, PA, 18947-1020
DUNS: 929950012
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Neeraj Sinha
 Principal Investigator
 () -
 sinha@craft-tech.com
Business Contact
 Paula Schachter
Title: Business Official
Phone: (215) 766-1520
Email: schachte@craft-tech.com
Research Institution
 University of Mississippi/National Center for Physical Acoustics
 Not M Available
 Coliseum Drive
University, MS, 38677
 (662) 915-5630
 Domestic nonprofit research organization
Abstract
The program focuses on turbulence modeling enhancements for predicting high-speed rocket base flows. A key component of the effort is the collection of high-fidelity data for supporting turbulence model validation and calibration. Base flow configurations of interest to NASA Marshal will also be investigated using improved modeling tools. Experiments for supersonic rocket base flows will be performed in the new 12”X12” tunnel, at the National Center for Physical Acoustics (NCPA), utilizing high-quality base flow models, provided by the US Army. Measurements will include Particle Image Velocimetry (PIV) for turbulent statistics, supplemented by Schlieren, Raman spectroscopy and Rayleigh scattering. Complimentary Large Eddy Simulations (LES) will provide additional turbulence statistics that are not readily/reliably measured. The data will support enhancements to the CRAFT Tech unified k-epsilon turbulence model. The impact of employing a variable turbulent Prandtl and Schmidt number methodology, based on a two-equation scalar variance framework, will be considered for reacting and non-reacting base flows. The effort will lead to extended validation of enhanced turbulence modeling tools, increased reliability of base drag & heat flux predictions and fills a major gap at NASA by improving upon base region simulation capabilities required for launcher design aerothermal predictions.

* information listed above is at the time of submission.

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