Application of an Interacting Boundary Layer Model to the Supersonic Turbulent Separation Problem.
CINCINNATI UNIV OHIO DEPT OF AEROSPACE ENGINEERING
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Numerical solutions to the supersonic interacting turbulent boundary layer equations are obtained for ramp induced separation problems. The method used is the alternating direction implicit scheme wherein a time-like relaxation process is followed to a sought after steady state. The turbulent structure of the flow is modeled with an eddy viscosity approach using both the equilibrium and relaxation models. Detailed comparisons of the present solution with experimental data and available Navier Stokes solutions show that this approach fails to predict the correct extent of upstream influence. The deficiency is traced to the absence of an imbedded shock wave in the interacting boundary layer model of the viscous region. Author
- Fluid Mechanics