Optimum lifting wings with specified longitudinal trim characteristics

The case of an infinitely slender wing that slightly disturbs a supersonic ideal gas flow is considered. The plan form and the free-stream Mach number M are given. The optimum surface of the wing y=g(x, z) is determined as a result of finding a bounded function of the local angles of attack _M=g(x, z)/x that minimizes the drag coefficient c_x for given values of the lift coefficient c_y and the pitching moment coefficient m_z. The problem is solved in the class of piecewise-constant functions for wings of complex geometry 1].Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 185–189, July–August, 1987.