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Optimization of wing parameters to achieve minimum weight at defined aerodynamic loads

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Abstract

The paper presents the method suitable for optimization of parameters and applied to design aircraft subassemblies on the example of a swept wing. It outlines the assumptions that are necessary to develop a mathematical model and describes constraints that served as the basis to develop an algorithm and describe the corresponding procedures in the GRIP (Graphics Interactive Programming) language that is a part of the CAD/CAM/CAE Unigraphics system. The further part of the study comprises discussion how the wing parameters and the mass functional are affected by the rigidity constraints and strength constraints. The algorithm for designing aircraft components was finally developed with inputs to the multi-criteria design process "Web Modelling" of an aircraft body. The study also includes initial assumptions to algorithms originally developed by the author and dedicated to the modelling of components incorporated into aircraft structures.

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... "The solution of the 1D simplified engineering model of the wing indicated that a constant taper wing, with straight leading edge and having a tip ratio of 0.4, gives the best aerodynamic performance" that was the statement of (Akwaboa et al. 2009) after his trials to optimize wing weight while preserving aerodynamic performance through applying wing taper. Kachel (2013) used taper ratio in distributing wing weight and confirmed its positive effect. Adler (1947) compared the effect of sweep on wings of constant aspect ratio at Mach 0.925, he found a significant drop in drag with increasing sweep angle, while the optimum lift he obtained was at 30 • of sweep. ...
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