The configuration and performance of the propulsion system for the hypersonic research vehicle are discussed. A study of the interactions between propulsion and aerodynamics of the highly integrated vehicle was conducted. The hypersonic research vehicle is configured to test the technology of structural and thermal protection systems concepts and the operation of the propulsion system under true flight conditions for most of the hypersonic flight regime. The subjects considered are: (1) research vehicle and scramjet engine configurations to determine fundamental engine sizing constraints, (2) analytical methods for computing airframe and propulsion system components, and (3) characteristics of a candidate nozzle to investigate vehicle stability and acceleration performance. (Author)


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    Title :

    Scramjet Nozzle Design and Analysis as Applied to a Highly Integrated Hypersonic Research Airplane


    Contributors:

    Publication date :

    1974


    Size :

    56 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Scramjet nozzle design and analysis as applied to a highly integrated hypersonic research airplane

    Small, William J. / Weidner, John P. / Johnston, P. J. | TIBKAT | 1976


    Scramjet integration on hypersonic research airplane concepts

    Weidner, J. P. / Small, W. J. / Penland, J. A. | NTRS | 1976