The method of integral relations has been used to compute the inviscid flow over a blunt body immersed in a nonuniform, expanding flow field. Emphasis has been placed on defining the flow environment experienced by a nose tip model in the exhaust plume of an underexpanded arc jet or rocket engine. Accordingly, the integral method has been formulated for an arbitrary description of a free stream which possesses both axial and radial gradients in Mach No., flow angle, total pressure, and total enthalpy.


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    The blunt body problem in nonuniform flow field

    LIN, T. / REEVES, B. / HOWY, D. et al. | AIAA | 1976


    Blunt-Body Problem in Nonuniform Flowfields

    T. C. Lin / B. L. Reeves / D. Siegelman | AIAA | 1977



    Blunt Body in Hypersonic Electromagnetic Flow Field

    Shang, J.S. | Online Contents | 2003


    Blunt Body in Hypersonic Electromagnetic Flow Field

    J. S. Shang / J. Hayes / J. Menart et al. | AIAA | 2003