Development of a Method for Predicting Subsonic Turbulent Separating Boundary Layers.
Final rept. 1 Sep 74-31 Dec 77,
AKRON UNIV OH DEPT OF MECHANICAL ENGINEERING
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An attempt is made to develop a method for predicting subsonic flows exhibiting pressure gradient induced turbulent boundary layer separation. The concept of a strong interaction between rotational viscous layer near a body and an external irrotational flow is adopted. The boundary layer approximations to the equations of motion are retained in the viscous layer mathematical coupling between the flow regions is introduced by requiring continuity of flow speed or Mach number and direction. An integral method is used to solve the boundary layer equations the equations are set up so that either flow speed or angle can be calculated, given the other. A modification of the wall-wake velocity profile valid for compressible flow is used together with an algebraic non-equilibrium turbulence model. Equations solved are the integral continuity, momentum, and moment of momentum equations. Predictions for compressible and incompressible plane two-dimensional separating and reattaching boundary layers are quite good when edge speed or angle are available from experimental data.
- Numerical Mathematics
- Fluid Mechanics