Normal force of a flat triangular wing in a supersonic flow

On the basis of an analysis of the results of numerical calculations for flow conditions with a forward shock wave attached to the leading edges, the dependence of the coefficient of the normal force of a flat triangular wing on the parameter sin is obtained in a wide range of change in the angle of attack, the angle of sweepback, and the Mach numbers.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 162–164, May–June, 1977.