The paper is devoted to an experimental study of laminar-turbulent transition in a three-dimensional supersonic boundary layer. The experiments were conducted at the low nose supersonic wind tunnel T-325 of ITAM at Mach numbers M=2 - 4. Model is a symmetrical wing with a 45° sweep angle, a 3 percent-thick circular-arc airfoil. The influence of flow parameters, such as the Mach number, unit Reynolds number, angle of attack, level of perturbations on the transitions to turbulence are on the consideration. Transition Reynolds numbers are obtained. Analysis of all obtained data allow to determine reliable value of Retr of swept wing supersonic boundary layer, that especially important at consideration of experiments fulfilled at different flow conditions in different wind tunnels.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    The influence of flow parameters on the transition to turbulence in supersonic boundary layer on swept wing


    Contributors:

    Conference:

    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


    Published in:

    Publication date :

    2016-10-13


    Size :

    6 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English





    NATURAL TRANSITION IN SUPERSONIC FLOWS: FLAT PLATE, SWEPT CYLINDER, SWEPT WING

    Archambaud, J. P. / Louis, F. / Seraudie, A. et al. | British Library Conference Proceedings | 2004


    STABILITY ANALYSIS OF SUPERSONIC SWEPT-WING BOUNDARY LAYERS

    Nomura, T. / AIAA | British Library Conference Proceedings | 2003


    Problem of calculation of swept-wing boundary-layer transition to turbulence at elevated freestream turbulence levels

    Kachanov, Y. S. / Borodulin, V. I. / Ivanov, A. V. | American Institute of Physics | 2016