Afterbody Boundary Layer Measurements in the Base Flow Facility

Krishnan, V and Mathur, NB (1997) Afterbody Boundary Layer Measurements in the Base Flow Facility. Technical Report. National Aerospace Laboratories, Bangalore,India.

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    Experiments were conducted to study the boundary layer properties on a cylindrical afterbody model in the Base Flow Facility. Measurements were made using a boundary layer pitot rake in the freestream Mach number range of 0.5 to 3.0. The ratio of the boundary layer thickness to the model diameter decreased from 6.5% to 2.5% in the above Mach number range. The mean velocity profiles showed that the boundary layer is turbulent and has features typical of a zero pressure gradient compressible turbulent boundary layer. The velocity profiles plotted in the wall-law co-ordinates show the existence of the logarithmic region with values of slope and intercept of 5.62 and 4.7 respectively.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Aftrbody;Compressible Turbulent Boundary Layer;Base Flow Facility
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Experimental Aerodynamics Division, Experimental Aerodynamics Division
    Depositing User: Mr. N A
    Date Deposited: 10 May 2006
    Last Modified: 24 May 2010 09:41

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