| Abstract: | A previous study by one of the present authors 1] listed a number of works dedicated to calculation of aerodynamic characteristics of aircraft of complex physical construction at supersonic velocities. A method for calculating the flow around a system of small-scale bearing surfaces was developed. The method reduces to determination of the velocity potential  with subsequent differentiation to determine pressure. The present study will present a method of calculating stationary aerodynamic characteristics of aircraft of extensive size at supersonic velocities, in which the basic unknown function is the perturbed pressure p . Eliminating numerical differentiation from the calculation permits an increase in accuracy of the results obtained. The problem is solved for an entire airplane with consideration of the craft's thickness.Translated from Ivestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 96–102, May–June, 1978. |
