In design of hypersonic space vehicles with ramjet propulsion, location of transition is important for heat transfer and performance of hypersonic inlets; however, there is no reliable theory to predict transition over 8 Mach; investigation was conducted in hypersonic shock tunnel at 8.5 to 10.5 Mach number range with stagnation temperature of 1400 K; experimental results obtained and comparison of transition Reynolds number are presented.


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    Titel :

    Boundary-layer transition on 10° cone in hypersonic flows


    Weitere Titelangaben:

    AIAA J


    Beteiligte:

    Erschienen in:

    AIAA Journal ; 3 , n 11


    Erscheinungsdatum :

    1965


    Format / Umfang :

    8 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Boundary-layer transition on a 10 deg cone in hypersonic flows.

    NAGAMATSU, H. T. / SHEER, R. W. | AIAA | 1965


    Boundary layer transition in hypersonic flows

    MALIK, M. / ZANG, T. / BUSHNELL, D. | AIAA | 1990



    Measurement on Transition of Hypersonic Boundary Layer Over Circular Cone

    Bi, Zhixian / Zhu, Nanji / Shen, Qing et al. | AIAA | 2007