Abstract
Abstract : The paper presents a computational method in the optimal bending- twisting comprehensive design of wings of subsonic and supersonic aircraft; a method for obtaining the finite fundamental solution is applied. By selecting a design point (M number and CL) at each of subsonic and supersonic aircraft, the designing of wings to withstand bending and twisting is carried out. The goal is to reduce lift-related drag. On this technical basis, the aerodynamic features of these two design points of subsonic and supersonic aircraft are noted in addition to the feasibility of other aircraft performance values applied to its structure. The paper presents the computational results of the optimal bending- twisting design for' subsonic aircraft, the optimal bending-twisting design of supersonic aircraft, as well as the comprehensive design. As analysis showed, the computational results are rational.
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