Assessment of boundary layer flow modeling approaches in computational fluid dynamics for compressible external aerodynamics using NACA-64618 Airfoil
In this work two dimensional CFD analysis have been carried out to predict the aerodynamic forces on the surface of the NACA 64618 airfoil at High Reynolds number of 9 million. The study focus on understanding the accuracy of the results obtained with different near wall modelling techniques. Computing the near wall flow region by two distinct approaches Viz. Direct resolution of shear stresses (Mentors SST Model) and use of wall function (K-ε Model) is assessed.CFD analysis results are compared with the wind tunnel test data available in the literatures. The reasons for deviation between CFD analysis results and wind tunnel test data are investigated and accurate procedure for modeling the near wall flow region is concluded.
Shankara Murthy.H.M, Madhukeshwara.N, S.Kumarappa