Influence of flow parameters and nose radius on laminar-turbulent transition location is under investigation. Experiments were conducted in shock tunnel at Mach number 6. Transition location was diagnosed by heat transfer rate distribution determined with aid of luminescent temperature converters. Model used was ogive-conical body of revolution having half angle about 9°. Through obtained Reynolds number range (up to Re∞,R = 3.44×105) no transition reversal was observed. Present data are in accordance with the hypothesis that transition reversal is due to formation of turbulence wedges in nosetip region. Highest observed transition onset Reynolds number was about Re∞,Xt ≈ 1.4×107 which is anomaly higher than conventional wind tunnel data for sharp cone at this Mach number range and lies in flight data region.


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    Title :

    Laminar-turbulent transition on a blunted ogive-conical body at hypersonic speeds


    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 :

    5 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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