Abstract
At the present times effective numerical methods have been developed for solving both steady-state and unsteady-state linear problems on the determination of the aerodynamic characteristics of wings of complex form, in a plan view [1–3]. The transition to three-dimensional systems requires the development of new methods. There are a number of known investigations in this direction, for simple three-dimensional configurations [4–7]. The present article proposes a method for solving supersonic problems of the determination of the steady-state and unsteady-state three-dimensional bearing systems. It is a development of known methods for calculating wings of complex form in a plan view. The most effective route is one based on a solution of the problem for stepwise dependences on the time. After this, the transition to any other laws is effected using a “packet” integral.
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