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Large-Eddy / Reynolds-Averaged Navier-Stokes Simulations of a Dual-Mode Scramjet CombustorNumerical simulations of reacting and non-reacting flows within a scramjet combustor configuration experimentally mapped at the University of Virginia s Scramjet Combustion Facility (operating with Configuration A ) are described in this paper. Reynolds-Averaged Navier-Stokes (RANS) and hybrid Large Eddy Simulation / Reynolds-Averaged Navier-Stokes (LES / RANS) methods are utilized, with the intent of comparing essentially blind predictions with results from non-intrusive flow-field measurement methods including coherent anti-Stokes Raman spectroscopy (CARS), hydroxyl radical planar laser-induced fluorescence (OH-PLIF), stereoscopic particle image velocimetry (SPIV), wavelength modulation spectroscopy (WMS), and focusing Schlieren. NC State's REACTMB solver was used both for RANS and LES / RANS, along with a 9-species, 19- reaction H2-air kinetics mechanism by Jachimowski. Inviscid fluxes were evaluated using Edwards LDFSS flux-splitting scheme, and the Menter BSL turbulence model was utilized in both full-domain RANS simulations and as the unsteady RANS portion of the LES / RANS closure. Simulations were executed and compared with experiment at two equivalence ratios, PHI = 0.17 and PHI = 0.34. Results show that the PHI = 0.17 flame is hotter near the injector while the PHI = 0.34 flame is displaced further downstream in the combustor, though it is still anchored to the injector. Reactant mixing was predicted to be much better at the lower equivalence ratio. The LES / RANS model appears to predict lower overall heat release compared to RANS (at least for PHI = 0.17), and its capability to capture the direct effects of larger turbulent eddies leads to much better predictions of reactant mixing and combustion in the flame stabilization region downstream of the fuel injector. Numerical results from the LES/RANS model also show very good agreement with OH-PLIF and SPIV measurements. An un-damped long-wave oscillation of the pre-combustion shock train, which caused convergence problems in some RANS simulations, was also captured in LES / RANS simulations, which were able to accommodate its effects accurately.
Document ID
20120001456
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Fulton, Jesse A. (North Carolina State Univ. Raleigh, NC, United States)
Edwards, Jack R. (North Carolina State Univ. Raleigh, NC, United States)
Hassan, Hassan A. (North Carolina State Univ. Raleigh, NC, United States)
Rockwell, Robert (Virginia Univ. Charlottesville, VA, United States)
Goyne, Christopher (Virginia Univ. Charlottesville, VA, United States)
McDaniel, James (Virginia Univ. Charlottesville, VA, United States)
Smith, Chad (Virginia Univ. Charlottesville, VA, United States)
Cutler, Andrew (George Washington Univ. Newport News, VA, United States)
Johansen, Craig (Calgary Univ. Alberta, Canada)
Danehy, Paul M. (NASA Langley Research Center Hampton, VA, United States)
Kouchi, Toshinori (Tohoku Univ. Sendai, Japan)
Date Acquired
August 25, 2013
Publication Date
January 9, 2012
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NF1676L-14004
AIAA Paper 2012-0115
Meeting Information
Meeting: 50th AIAA Aerospace Sciences Meeting and Exhibit
Location: Nashville, TN
Country: United States
Start Date: January 9, 2012
End Date: January 12, 2012
Funding Number(s)
CONTRACT_GRANT: FA 9550-09-1-0611
WBS: WBS 599489.02.07.07.02.21.22
Distribution Limits
Public
Copyright
Public Use Permitted.

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