Upper estimates of airfoil aerodynamic characteristics for a viscous incompressible flow

Abstract

In the present work the method of the inverse boundary-value problems is used to obtain upper estimates for two main integral airfoil characteristics: lift coefficient Cl and the aerodynamic ratio K in a certain class of airfoils flown by an incompressible flow of viscous fluid at a fixed angle of attack at high Reynolds number (106-107) with the presence of a thin non-separating turbulent boundary layer.