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.


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    Title :

    Rocket-Based Combined Cycle Engine Technology Development: Inlet CFD Validation and Application


    Contributors:
    J. R. Debonis (author) / S. Yungster (author)

    Publication date :

    1996


    Size :

    21 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Rocket-Based Combined Cycle Engine Technology Development - Inlet CFD Validation and Application

    DeBonis, J. R. / Yungster, S. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 1996




    Rocket-Based Combined-Cycle Engine Technology Development - Sub-Scale Inlet Experimental Results

    Fernandez, R. / Trefny, C. J. / Thomas, S. R. et al. | British Library Conference Proceedings | 1997