Abstract

In this paper, an expansion of my research work [1] we complete a numerical investigation of lift and drag performance of the NACA0012 airfoil at a different negative and positive angle utilizing computational fluid dynamic. This investigation of the two dimensional (2D) subsonic fluid flow over an airfoil at an alternate approach extending from negative angle - 6 degree to positive point 10 degrees (distinction of 2 degrees AoA) at consistent Mach number is available. For this testing and investigation, we utilized a model of K-ω SST turbulence. The final product of the analysis, computational fluid dynamic reenactment demonstrates the applicability to the energizing finding the literature. Through this testing, we are communicating a dependable option test technique for discovering coefficient of drag and lift.

Authors and Affiliations