Abstract
This paper investigates modelling strategies on the prediction of lift and drag coefficients of a NACA0012 airfoil at Reynolds number of 360,000. Two computational methods are employed; namely Navier-Stokes equation and panel method, by using different tools for computing lift and drag coefficients. The obtained results are compared against experiment in order to assess the accuracy of each technique. Two turbulence models are employed; Reynolds stress model, which is not based on Boussinesq assumption and accounts for flow anisotropy and realizable model which is based on the Boussinesq assumption for computing Reynold stresses. Grid independent solution is produced using the 2-D URANs by employing the fitting method and the obtained lift and drag coefficients are compared against experiment. The fitting method is found to be efficient in saving computational time and power. It is also found that Boussinesq approximation is efficient in predicting lift coefficient. However, the 3rd order panel method produced a remarkably accurate drag coefficient compared to other investigated computational models. Combining the findings of this paper with the existing computational methods in the literature would significantly in improve the accuracy of predicting lift and drag coefficients and may significantly enhance the accuracy of simulation of several aerodynamics applications.