PREDICTION OF SEPARATED TRANSONIC WING FLOWS WITH NONEQUILIBRIUM ALGEBRAIC TURBULENCE MODEL

A nonequilibrium algebraic turbulence model, which is based on the turbulence closure scheme of Johnson and King, is proposed to predict separated transonic wing flows. The influence of history effects are modeled by solving a partial differential equation for the maximum Reynolds shear stress, which is then used to scale the eddy viscosity of an algebraic model. The turbulence model is implemented in a three-dimensional, Reynolds-averaged Navier- Stokes code. Comparisons with experimental data are presented which show clearly that the nonequilibrium type of turbulence model is essential for accurate prediction of transonic separated flows. © 1990 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.