Numerical simulation of supersonic flow using a new analytical bleed boundary condition | Zendy

G. J. Harloff | Zendy; Graeme E. Smith | Zendy

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Numerical simulation of supersonic flow using a new analytical bleed boundary condition

Author(s) -

G. J. Harloff,

Graeme E. Smith

Publication year - 1995

Publication title -

31st joint propulsion conference and exhibit

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1995-2759

Subject(s) - supersonic speed , bleed , computer science , choked flow , boundary value problem , mechanics , flow (mathematics) , computer simulation , aerospace engineering , physics , mathematics , engineering , mathematical analysis , medicine , surgery

A new analytical bleed boundary condition is used to compute flowfields for a strong oblique shock wave/boundary layer interaction with a baseline and three bleed rates at a freestream Mach number of 2.47 with an 8 deg shock generator. The computational results are compared to experimental Pitot pressure profiles and wall static pressures through the interaction region. An algebraic turbulence model is employed for the bleed and baseline cases, and a one equation model is also used for the baseline case where the boundary layer is separated.

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