A CFD methodology has been developed for inlet analyses of Rocket-Based Combined Cycle (RBCC) Engines. A full Navier-Stokes analysis code, NPARC, was used in conjunction with pre- and post-processing tools to obtain a complete description of the flow field and integrated inlet performance. This methodology was developed and validated using results from a subscale test of the inlet to a RBCC 'Strut-Jet' engine performed in the NASA Lewis 1 x 1 ft. supersonic wind tunnel. Results obtained from this study include analyses at flight Mach numbers of 5 and 6 for super-critical operating conditions. These results showed excellent agreement with experimental data. The analysis tools were also used to obtain pre-test performance and operability predictions for the RBCC demonstrator engine planned for testing in the NASA Lewis Hypersonic Test Facility. This analysis calculated the baseline fuel-off internal force of the engine which is needed to determine the net thrust with fuel on.
Rocket-Based Combined Cycle Engine Technology Development: Inlet CFD Validation and Application
1996
21 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Aerodynamics , Fluid Mechanics , Computational fluid dynamics , Computational grids , Engine inlets , Flow distribution , Hypersonic flow , Navier-stokes equation , Pressure distribution , Rocket engine design , Rocket engines , Static pressure , Drag , Engine tests , Momentum , Supersonic wind tunnels , Surface properties , Wind tunnel tests
Rocket-Based Combined Cycle Engine Technology Development - Inlet CFD Validation and Application
British Library Conference Proceedings | 1996
|Rocket-Based Combined-Cycle Engine Technology Development - Sub-Scale Inlet Experimental Results
British Library Conference Proceedings | 1997
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