Dual-Mode Scramjet Combustor: Numerical Analysis of Two Flowpaths

A review of numerical simulation and modeling of combustion in scramjets

“…In addition, the calibrated Schmidt number of 0.7 was acceptable for the case in which a divergent combustor was tested. 11 In conclusion, the turbulent Schmidt number yielded predicted peak pressure values that agreed within 1% of the experimental data and proved to be acceptable for two different tested equivalence ratios (0.5 and 1.0) and two different combustor configurations (step combustor and divergent combustor). 11 Other work investigating turbulence modeling is that of Ghodke et al 13 who investigated LES of supersonic combustion in a cavity-based flameholder.…”

“…Milligan et al utilized a constant, calibrated turbulent Schmidt number in order to establish a baseline numerical approach for examining the efforts in RC22. 11,12 A calibrated turbulent Schmidt number equal to 0.7 predicted the peak pressure within 1% of the experimentally measured pressure for two different testing conditions. 11 The first condition had an equivalence ratio of 0.5 and the second had an equivalence ratio of 1.0.…”

“…11,12 A calibrated turbulent Schmidt number equal to 0.7 predicted the peak pressure within 1% of the experimentally measured pressure for two different testing conditions. 11 The first condition had an equivalence ratio of 0.5 and the second had an equivalence ratio of 1.0. These results are shown in Figures 11 and 12.…”

“…The unified model was able to reliably address these needs and showed to be reliable in the types of flows that were analyzed. 10 Recent work by Milligan et al 11 revealed insights into the significance of modeling parameters as well, specifically the Schmidt number. Milligan et al conducted work that involved numerical characterization of a supersonic wind-tunnel facility, Research cell (RC22), at a U.S. Air Force Research Laboratory.…”

“…The benefits are as follows: it eliminates challenges induced by corner effects; it is more efficient in heat load distribution; and reduces weight. 11 The circular flow path does poses challenges with regard to fuel penetration into the air stream and flame propagation.…”