Hypersonic boundary layer stability and transition were studied experimentally and numerically for the test case of 7° cone model with blunt nose-tip. The experiments were performed for M=6, heat flux distributions and wall pressure pulsations were measured. It was obtained that the angle of cover and size of bluntness significantly affects on the transition location.

    Real hypersonic vehicle is equipped by thermal protection systems (TPS) which have a surface roughness (joints and connecting elements). Furthermore the surface of the elements of TPS is not smooth and has some relatively uniform roughness, which can vary during flight. Roughness size can change during thermal ablation or destruction, in addition elements of isolated roughness comparable with a thickness of the boundary layer may appear on surface (caverns, ledges, etc.,). These elements are additional receptivity areas where the additional perturbations are generated and developing in boundary layer that may cause premature laminar-turbulent transition. This effect has been studied for more than 50 years [17-3], but almost all the work devoted to the search of engineering correlations, but not to receptivity or stability problems. This effect needs to be studied more precisely.


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    Title :

    Effect of roughness of the blunted cone nose-tip on laminar-turbulent transition


    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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