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High Performance Simulation Tool for Multiphysics Propulsion Using Fidelity-Adaptive Combustion Modeling

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX17CS15P
Agency Tracking Number: 170058
Amount: $124,995.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: T1.02
Solicitation Number: N/A
Solicitation Year: 2017
Award Year: 2017
Award Start Date (Proposal Award Date): 2017-06-09
Award End Date (Contract End Date): 2018-06-08
Small Business Information
3221 North West 13th Street, Suite A
Gainesville, FL 32609-2189
United States
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Siddharth Thakur
 Principal Investigator
 (352) 271-8841
Business Contact
 Siddharth Thakur
Title: Business Official
Phone: (352) 271-8841
Research Institution
 Stanford University
 Michala Welch
3160 Porter Drive, Suite 100
Palo Alto, CA 94304-8445
United States

 (650) 736-7736
 Domestic Nonprofit Research Organization

The innovation proposed here is a fidelity-adaptive combustion model (FAM) implemented into the Loci-STREAM CFD code for use at NASA for simulation of rocket combustion. This work will result in a high-fidelity, high-performance multiphysics simulation capability to enhance NASA's current simulation capability of unsteady turbulent reacting flows involving cryogenic propellants. This novel FAM model utilizes a combustion submodel assignment, combining flamelet-based combustion models (such as inert-mixing models, equilibrium chemistry, diffusion-flame Flamelet/Progress Variable (FPV) or premixed-flame models) for the computationally efficient characterization of quasi one-dimensional, steady, and equilibrated combustion regimes, with combustion models of higher physical fidelity (such as thickened flame models, reduced/lumped chemistry models) for accurate representation of topologically complex combustion regions (associated with flame-anchoring, autoignition, flame-liftoff, thermoacoustic coupling, and non-equilibrium combustion processes) that are not adequately represented by the current flamelet model in Loci-STREAM. In FAM, the selection of a combustion submodel from a set of models available to a CFD-combustion solver is based on user-specific information about quantities of interest and a local error control. With this information, FAM performs an identification procedure for an optimal combustion submodel assignment from the available combustion models that. This simulation capability will have direct impact on NASA's ability to assess combustion instability of rocket engines.

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

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