Solution of the Inverse Boundary Value Problem of Aerohydrodynamics for a Two-Element Airfoil

The basic inverse boundary value problem of aerohydrodynamics for a two-element airfoil is analytically and numerically solved in the complete formulation. The problems of designing biplane airfoils and an airfoil with a trailing-edge flap or leading edge flap (slat) are solved for a given distribution over the unknown contours of the velocity or the pressure as a function of the contour arc abscissa of the airfoils which depends on a finite number of the parameters.