Airfoil smoothing using unconditional optimization taking into account aerodynamic criteria

Abstract

The smoothing of airfoils in sections of the surface of an aircraft wing is considered. The issue of using the distribution of pressure and Mach number along the chord of an airfoil as criteria for smoothing efficiency is being studied. Smoothing is considered as a problem of unconditional minimization of a quadratic objective function. The arguments of the objective function are the second derivatives of the tabular function interpolating the contour of the airfoil. Minimization is performed using the gradient descent method.