With results of testing various models for several last years, the article will describe the capabilities of the IT-302M hotshot wind tunnel in terms of modeling of high-velocity flows in the Mach number range from 4 to 20 for external flow regimes and from 2 to 6 for the attached pipeline regime with the following flow parameters: total pressure from 5 to 1000 bar and total temperature from 700 to 3500 K. Some of these pioneering activities are unique: for instance, a positive thrust force was obtained in a scramjet model for the first time; a series of tests was performed for comparisons of the results of inlet flows obtained in hotshot and blow down wind tunnels, including shock starting of the inlet and a possibility of its modeling by using a special device in the long-duration wind tunnel. A new concept of a short-duration wind tunnel with opposing pistons of pressure multipliers has been considered.


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    Titel :

    IT-302M hotshot wind tunnel as a tool for the development of hypersonic technologies


    Beteiligte:
    Goldfeld, M. A. (Autor:in) / Maslov, A. A. (Autor:in) / Starov, A. V. (Autor:in) / Shumskii, V. V. (Autor:in) / Yaroslavtsev, M. I. (Autor:in) / Fomin, Vasily (Herausgeber:in)

    Kongress:

    INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2016): Proceedings of the 18th International Conference on the Methods of Aerophysical Research ; 2016 ; Perm, Russia


    Erschienen in:

    Erscheinungsdatum :

    13.10.2016


    Format / Umfang :

    8 pages





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    Hotshot Wind Tunnel Force Measurement

    Berry, J. / Hoarau, R. | IEEE | 1965



    Scramjet Tests in the ONERA F4 Hotshot Wind Tunnel

    Viguier, Paul / Garraud, Julien / Soutade, Jacques et al. | AIAA | 2014


    Improved method of determining flow parameters in a hotshot wind tunnel

    Gavrishev, A. A. / Tsyryulnikov, I. S. | American Institute of Physics | 2016