The work is devoted to the experimental study of the development of mass flow and total temperature pulsations in the boundary layers of a flat plate and a swept wing at Mach numbers 2, 2.5 and 4. The experiments were carried out in a T-325 supersonic wind tunnel of the ITAM SB RAS. The pulsations were measured using a constant temperature hot-wire anemometer in the automatic scanning mode based on probe overheating. The analysis of the experimental data showed that for the experimental conditions at all stages of the laminar-turbulent transition of boundary layers, the mass flow and total temperature pulsations develop similarly, and the ratio of the pulsation levels practically does not change.


    Access

    Access via TIB


    Export, share and cite



    Title :

    Investigation of laminar-turbulent transition of supersonic boundary layer by scanning constant temperature hot-wire anemometer at Mach 2-4


    Contributors:

    Conference:

    INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2020) ; 2020 ; Novosibirsk, Russia


    Published in:

    Publication date :

    2021-05-24


    Size :

    4 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Numerical Simulations of Laminar-Turbulent Transition In Supersonic Boundary Layer

    Jiang, Li / Choudhari, Meelan / Chang, Chau-Lyan et al. | AIAA | 2006


    Numerical Simulations of Laminar-Turbulent Transition In Supersonic Boundary Layer

    Jiang, L. / Choudhari, M. / Chang, C. et al. | British Library Conference Proceedings | 2006



    NUMERICAL INVESTIGATION OF LAMINAR-TURBULENT TRANSITION IN A CONE BOUNDARY LAYER AT MACH 6

    Sivasubramanian, J. / Fasel, H. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2011