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Abstract
The previously developed iteration method of the wing geometry construction by the given pressure distribution in the compressible viscous flow is applied to the wing in the full configuration of the subsonic aircraft including pylons and engine nacelles. The algorithm of the residual correction is used in which the direct calculation of the configuration in the frames of the averaged Navier-Stokes equations is carried out turn by turn with the geometry correction which reduces the discrepancy between the current and the target pressure distribution. As a correction block, the previously developed method for solving the inverse problem for a wing in the same configuration (but without a pylon) in a compressible gas potential flow is used, taking into account the influence of the thickness of the displacement of the boundary layer and the wake of the wing. Examples of wing geometry design with given pressure distribution showing high speed of convergence (three to eight iterations) are presented.
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