Computational Tool for Coupled Simulation of Nonequilibrium Hypersonic Flows with Ablation

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$599,980.00
Award Year:
2011
Program:
SBIR
Phase:
Phase II
Contract:
NNX11CA27C
Award Id:
n/a
Agency Tracking Number:
094560
Solicitation Year:
2009
Solicitation Topic Code:
X9.01
Solicitation Number:
n/a
Small Business Information
AL, Huntsville, AL, 35805-1944
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
Y
Duns:
185169620
Principal Investigator:
RANJAN MEHTA
Principal Investigator
(256) 726-4964
sxh@cfdrc.com
Business Contact:
Silvia Harvey
Business Official
(256) 726-4858
sxh@cfdrc.com
Research Institution:
Stub




Abstract
The goal of this SBIR project is to develop a predictive computational tool for the aerothermal environment around ablation-cooled hypersonic atmospheric entry vehicles. This tool is based on coupling the relevant physics models to the LeMANS code for hypersonic flows and to the MOPAR code for material response, both developed by the University of Michigan. In Phase I of this project, we developed an efficient, high-fidelity 3-D radiation transfer equation (RTE) solver based on the Modified Differential Approximation (MDA). The MDA method was shown to be accurate over at least three orders of magnitude variation in medium optical thickness, typical in entry hypersonic flows. The coupled LeMANS-radiation code was demonstrated for Stardust and IRV2 configurations, while the coupled LeMANS-MOPAR code was validated for the Passive Nosetip Technology (PANT) experiment [1], successfully establishing feasibility. In Phase II, the primary focus is to advance the flow and ablation modeling capabilities of the LeMANS/MOPAR codes by including innovative models for: (1) Non-equilibrium surface thermochemistry; (2) Non-equilibrium pyrolysis chemistry; and (3) Non-gray, non-equilibrium radiation. All models will be implemented in a modular manner with particular attention paid to their coupling interfaces to facilitate easy coupling to a computational aerothermodynamics code of interest to NASA such as DPLR. The tool will be validated and applied to ablation-cooled re-entry flow problems relevant to NASA such as the Stardust capsule.

* information listed above is at the time of submission.

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