|PROPOSAL NUMBER:||04-II T8.02-9927|
|PHASE-I CONTRACT NUMBER:||NNM05AA64C|
|RESEARCH SUBTOPIC TITLE:||Advanced High Fidelity Design and Analysis Tools For Space Propulsion|
|PROPOSAL TITLE:||Base Flow Model Validation|
|SMALL BUSINESS CONCERN (SBC):||RESEARCH INSTITUTION (RI):|
|NAME:||Combustion Research and Flow Technology,||NAME:||University of Mississippi/National Center for Physical Acoustics|
|ADDRESS:||6210 Kellers Church Road||ADDRESS:||Coliseum Drive|
|STATE/ZIP:||PA 18947-1020||STATE/ZIP:||MS 38677-0448|
|PHONE:||(215) 766-1520||PHONE:||(662) 915-5630|
PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name,Email)
TECHNICAL ABSTRACT ( Limit 2000 characters, approximately 200 words)
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 12Â”X12Â” 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.
POTENTIAL NASA COMMERCIAL APPLICATIONS ( Limit 1500 characters, approximately 150 words)
The proposed effort is directly supportive of NASAÂ’s activities related to the design. testing and flight certification of future generations of space vehicles, e.g. Crew Launch Vehicle (CLV), Heavy Launch Vehicle (HLV), etc. Specifically, to accurately develop thermal protection systems (TPS) and establish base heat shield requirements will require a basic understanding of the physical mechanisms governing radiative and convective heat transfer resulting from the plume aerothermal environments. The proposed simulation tool, that will be well-validated against test-data, will play a crucial role in supporting production-oriented analysis relevant to design optimization, definition of test procedures, supporting launch requirements and test data interpretation.
POTENTIAL NON-NASA COMMERCIAL APPLICATIONS ( Limit 1500 characters, approximately 150 words)
The base flow modeling capability development is directly applicable to major DoD initiatives of current relevance. Specifically, it supports missile plume signature characterization of tactical/strategic systems as related to Missile Defense Agency (MDA) requirements for Boost Phase Intercept (BPI) and threat detection via signature spike (Â“launch flashÂ”) during missile engine ignition. The simulation tools are directly applicable to the development of commercial launch vehicles, and supporting analysis related to design of thermal protection systems (TPS). The simulation software will be licensed to prime vendors and supporting organizations engaged in development of commercial launchers, missiles and interceptors, propulsion systems for space applications e.g. Boeing/Rocketdyne, Pratt & Whitney, Northrop Grumman, Lockheed, Raytheon, etc.