Experimental data and results of numerical simulation of a supersonic flow over a blunt cone are presented. Experimental investigations of the effect of local cooling or heating of the nose of the model on the laminar-turbulent transition on sharp and blunt cones were carried out in two hypersonic wind tunnel ITAM SB RAS - IT-302M and “Transit-M.” Numerical simulation were performed using the commercial package ANSYS Fluent and transition modelγ- Reθt. The computed results of the heat flux on the cone surface are compared with the data of wind tunnel experiments performed at the flow Mach number М = 5.8 and 5.95. It is shown an ambiguous effect of local impact for different conditions of the flow.


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    Title :

    Effect of local heating/cooling on the laminar-turbulent transition on a blunted cone


    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





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