Abstract: | Infinitely thin wings weakly perturbing a supersonic flow of perfect gas are investigated. The flow problem is solved in a linear formulation 1]. The shape of the wing in plan and the Mach number M of the oncoming flow are specified. The optimal wing surface is determined as a result of finding the function of the local angles of attack M(x, z) which ensures a minimum of the drag coefficient cx when there are limitations in the form of equalities on the lift coefficient cy and the pitching moment mz. A separationless flow regime is realized on the optimal wing for the given number M , and its subsonic leading edge does not experience a load 2].Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 6, pp. 154–160, November–December, 1985. |