NASA NTRS · 19920035234
CFD evaluation of Mach 17 HYPULSE scramjet combustor data
Abstract
Three-dimensional finite rate chemistry solutions are performed on a single fuel injector configuration. The results are compared with limited experimental data obtained from the HYPULSE expansion tube facility at simulated flight Mach 17 flow conditions. All comparisons, except for wall heat flux, were in excellent agreement. Key findings from this study are useful in interpretation of the experimental measurements.
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Bobskill, Glenn J., Bittner, Robert D., Riggins, David W., Mcclinton, Charles R.. 1991-12-01. CFD evaluation of Mach 17 HYPULSE scramjet combustor data. https://ntrs.nasa.gov/citations/19920035234
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