Results of numerical and experimental investigations of steady state supersonic viscous corner flows in simplified geometries that resemble typical wing body–fuselage intersections are presented. These flows are numerically calculated using the computational fluid dynamics code of Fluent and include the use of standard turbulence models. Experimental work includes the use of the oil film flow visualization technique to visualize the surface flow patterns. The flows considered are symmetric about the corner bisector. This article focuses on the development of the three shock structure along the various geometries, specifically focusing on the formation and growth of the shear layers that result from the Mach reflection. The resultant effects of this shear layer on pressure distributions, shear stress, and changes in Mach numbers are discussed. The shock wave boundary layer interaction is also presented.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Supersonic viscous corner flows


    Contributors:
    Naidoo, P (author) / Skews, B W (author)


    Publication date :

    2012-08-01


    Size :

    16 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown




    Supersonic viscous corner flows

    Naidoo, P | Online Contents | 2012





    Vortical Solutions in Supersonic Corner Flows

    Marsilio, R. | Online Contents | 1993