A one equation turbulence model based on the turbulent kinetic energy equation is presented. The model is motivated by the success of the Johnson-King model and is developed from the available experimental observations on both attached and separated turbulent flows. Results for both attached and separated flow about the NACA 0012 and RAE 2822 airfoils are compared with the Baldwin-Lomax algebraic turbulence model, the q-omega two equation model, the Johnson-King model and available experimental pressure and skin friction data. Based on the results obtained, the model duplicates the success of algebraic models in attached flow cases. For separated flow cases, it predicts shock location and strength closer to the experimentally observed values than both the algebraic and two equation models. However, the model suffers some limitations in predicting shock location for transonic cases with large shock induced separation.
A one equation turbulence model for transonic airfoil flows
Aus einer Gleichung bestehendes Turbulenzmodell fuer die Stroemungsvorgaenge an Ueberschallflugzeugen
AIAA-Papers ; Jan ; 1-12
1988
12 Seiten, 12 Bilder, 14 Quellen
Conference paper
English