Surface design of the wing with horizontal tail in transonic cruise flight

The method of profiles design of the wing and horizontal tail configuration is considered. The minimum induced and wave losses in balanced transonic cruise flight for a fixed lift coefficient and Mach number are achieved. The wing and tail plan forms and thickness distribution are constant. The method consists of the direct aerodynamic calculation of the wing tail configuration based on the solution of a full velocity potential equation, analytical approximation of the wing sections profiles and the extremum seeking algorithm. The target function is the product of the maximum local Mach number and the induced drag of the wing tail configuration. The results of designing the wing tail configuration for a typical passenger aircraft are show.