Application of Wray-Agarwal Algebraic Transition Model for Transitional Flow over 2D NLF (1) - 0416 Airfoil

The Wray-Agarwal Algebraic Transition (WA-AT) model has been validated for various ERCOFTAC flat plate cases and symmetric NACA airfoil cases. The NLF (1) - 0416 is an asymmetric airfoil with unique laminar to turbulent transition characteristics. The NLF (1) -0416 was chosen as a validation test case by the AIAA 1st Transition modelling workshop. This paper presents the results of the validation of the Wray-Agarwal Algebraic Transition model for the NLF (1) - 0416 airfoil. The WA-AT model shows excellent agreement with experimental data for the predictions of lift coefficient, drag polar, and transition location for angles of attack from -6 to 14 degrees. The experimental Reynolds number is 4*10^6 with a turbulence intensity of 0.15%. In addition, computed validation results show that the WA-AT predictions demonstrate minimal dependence on mesh refinement. Results are presented for three meshes of sufficient refinement, all of which are similar in refinement to the 1st AIAA Transition Workshop guidelines. Overall, the WA-AT model shows excellent agreement with experimental data and shows minimal prediction sensitivity to mesh refinement.