A 'sublayer-mass flow' method is developed as a new tool for analysis of crossflow separation on a tangent-ogive forebody at high angle of attack. The sublayer-mass flow is defined as the mass efflux in the axial direction through a small control surface perpendicular to the body surface. From the visualization of the flow field, which is computed using the thin-layer Navier-Stokes approximation with the Baldwin-Lomax turbulence model, it is found that the critical points (i.e. the local minima) of sublayer-mass flow are located at the points of convergence of surface streamlines. Thus, the critical points indicate where the flow is separated. This representation can be used to identify the primary and secondary separation points of crossflow separation. The results obtained for a Mach number of 0.2, a Reynolds number of 1.3 x 106 and an angle of attack of 35 degree show a a primary separation line originating from the nose tip and a secondary separation line which originates at about 1.25 diameter behind the nose tip. This is the first successful capture of crossflow separation points in a three-dimensional flow computation.


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    Title :

    Numerical investigation of crossflow separation on a tangent-ogive forebody at high angle of attack


    Additional title:

    Numerische Untersuchung der Strömungsablösung an Rotationskörpern (Tangentialogiven) mit großen Anstellwinkeln


    Contributors:
    Onn, S.C. (author) / Yang, N.C. (author) / Hsiung, J.L. (author) / Wei, C.K. (author)


    Publication date :

    1997


    Size :

    6 Seiten, 10 Bilder, 14 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English







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