A comparative study of scramjet injection strategies for high Mach numbers flowsA simple method for predicting the axial distribution of supersonic combustor thrust potential is described. A complementary technique for illustrating the spatial evolution and distribution of thrust potential and loss mechanisms in reacting flows is developed. Wall jet cases and swept ramp injector cases for Mach 17 and Mach 13.5 flight enthalpy inflow conditions are numerically modeled and analyzed using these techniques. The visualization of thrust potential in the combustor for the various cases examined provides a unique tool for increasing understanding of supersonic combustor performance potential.
Document ID
19920066252
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Riggins, D. W. (Missouri-Rolla, University Rolla, United States)
Mcclinton, C. R. (NASA Langley Research Center Hampton, VA, United States)
Rogers, R. C. (NASA Langley Research Center Hampton, VA, United States)
Bittner, R. D. (Analytical Services and Materials, Inc. Hampton, VA, United States)