Thin-layer approximation and algebraic model for separated turbulentflows

TLDR

The model’s applicability to other cases is explored in companion papers. The study introduces an algebraic turbulence model for two‑ and three‑dimensional separated flows that eliminates the need to locate the boundary‑layer edge. Model properties were calibrated and validated against experiments involving an incident shock on a flat plate, a compression‑corner separated flow, and transonic airfoil flow. Numerical Navier‑Stokes predictions of separation and reattachment points agree with experiments within one boundary‑layer thickness, and applying law‑of‑the‑wall boundary conditions does not significantly affect these predictions.

Abstract

An algebraic turbulence model for two- and three-dimensional separated flows is specified that avoids the necessity for finding the edge of the boundary layer. Properties of the model are determined and comparisons made with experiment for an incident shock on a flat plate, separated flow over a compression corner, and transonic flow over an airfoil. Separation and reattachment points from numerical Navier-Stokes solutions agree with experiment within one boundary-layer thickness. Use of law-of-the-wall boundary conditions does not alter the predictions significantly. Applications of the model to other cases are contained in companion papers.