The design and analysis of scramjet engines relies heavily on the use of Computational Fluid Dynamics (CFD) methods due to the lack of experimental facilities and engineering analysis techniques for high Mach number, high temperature flows. This emphasis on CFD requires that the methods be calibrated through comparison with existing experimental data to determine their level of capability and range of applicability. At General Dynamics' Fort Worth Division a level of confidence has been established in the use of CFD methods for scramjet flowfields. These methods include a Beam-Warming based Unsteady Navier-Stokes (UNS) solver, a Beam-Warming based Parabolized Navier-Stokes (PNS) solver, and a MacCormack based PNS solver. Specifically, comparisons between CFD flowfiels and experimental data for a blunt cone at Mach 10.6, an inlet at Mach 7.4, a combustor at Mach 2.4, and an axisymmrtric plug nozzle at Mach 3.2 have been made. These claibrations show good overall agreement for wall pressures, integrated forces, and pressure, Mach number, and chemical species profiles. Examination of the disparities between the CFD and experimental results focuses concern on the treatment of boundary layer turbulence and finite rate chemistry. As a result, further development tasks are suggested which, when complete, will further enhance the applicability of the subject CFD methods.
Calibration of CFD methods for high Mach number aeroengine flowfields
Kalibrierung von Methoden zur Fluiddynamikberechnung fuer Flugmotoren-Stroemungsfelder bei hohen Machzahlen
ASME-Papers ; Jun ; 1-8
1988
8 Seiten, 19 Bilder, 14 Quellen
Aufsatz (Konferenz)
Englisch
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