Comprehensive numerical study of difference between the aerodynamic coefficients in symmetrical classic airfoil with two different assumptions of transitional and fully turbulent flows in both of compressible and incompressible regimes

In the following paper, the accuracy of full turbulent K-e and transitional K-w models in external aerodynamic capturing of NACA0012 in both incompressible regime (Re number of 6 million) and subsonic compressible regime (Mach number of 0.3 to 0.9 and Re number of 1 million to 100 million) have been comprehensively investigated until using comparison between both results, the differences between full turbulent and transitional flow (combined fully laminar + transition region + fully turbulent) assumptions in aerodynamic coefficients specified accurately. Among these investigations, some sorts of sensitivity analysis, including changes in free-stream Mach number, free-stream Reynolds number, free-stream angle of attack, grid density and free stream turbulence level have been done. Also the effects of transition inception point and affecting parameters, and the magnitude of the conformity between numerical results and theoretical concepts about transition and related effective parameters on the magnitude of lift, drag, lift-slope, pressure distribution, and pressure/friction lift-and-drag coefficients have been investigated in detail. To confirm the validity and the accuracy of the results, the numerical results have been compared with some published references.