The direct method for a wide range of 3D aerodynamic forms optimal design based on the approximation of required geometry with the help of Bezier ? Bernstein surfaces is developed. Its high efficiency was shown during solving the problem of optimal axisymmetric Laval nozzle supersonic part of maximum thrust design. Suggested method is applied to 3D transition channels design, to ramjet 3D nozzle design and to the supersonic part of 3D nozzle from compact multiple-jet configuration design. For more detailed description of shapes variety the required geometry description technique modification ? non-uniform Bezier ? Bernstein surface is offered. Obtained results demonstrate the ability of the suggested method to be applied to different 3D configurations design problems solving.
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