Design and computational analysis of NACA 846A110 and NACA 837A110 airfoils

Abstract

Previous experimental research [1] has shown that the National Advisory Committee for Aeronautics (NACA) 8 - series airfoils have high critical and drag divergence mach numbers compared to NACA 6 - series airfoils. By varying the minimum pressure locations, new such type of airfoils can be obtained. The newly designed airfoils are meshed and analyzed computationally using compressible solver settings and k-€ turbulence model. The above mentioned airfoils are submerged in flow fields of various Mach numbers and angle of attacks. The force and moment coefficients such as C <inf xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">l</inf> , C <inf xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">d</inf> are monitored and graphs have been plotted between each of the above coefficients and Mach number. The results are interpreted both graphically and analytically, and it is found that the critical Mach number is 0.7277 and 0.7645 for NACA 846A110 and NACA 837A110 airfoils respectively and the drag divergence Mach number is 0.785 and 0.794 for NACA 846A110 and NACA 837A110 airfoils respectively. <sup xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">1 2</sup>