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JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A 2013, Vol. 39 Issue (3) :320-324    DOI:
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Wing geometric twist design method based on lifting-line theory
Qiao Yuhang1, Ma Dongli1, Deng Xiaogang2*
1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. State Key Laboratory of Aerodynamics, China Aerodynamics Research & Development Center, Mianyang 621000, China

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Abstract To meet the demand for reducing induced drag in aircraft design, a geometric twist design method for the wing was proposed, based on the research of three-dimensional wing induced drag in lifting-line theory. This method with input parameters of wing total lift, wing planar shape, airfoil aerodynamic characteristics, gives the wing geometric twist result. In low speed situations, a wing with elliptical lift distribution, which had the minimum induced drag,was obtained. Far-field method was used to calculate induced drag, CATIA parametric method was developed for automatic wing generation, script language of ICEM tool was applied for automatic grid generation, symbolic computation capability of MATLAB was carried out to perform the program. This method is suitable for geometric twist design of straight wing in low-speed viscous flow. Examples indicated that the wing designed by this method had an elliptical lift distribution, thereby had lower induced drag.
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Keywordslifting-line theory   geometric twist   lift distribution   induced drag     
Received 2012-03-13;
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Qiao Yuhang, Ma Dongli, Deng Xiaogang.Wing geometric twist design method based on lifting-line theory[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2013,V39(3): 320-324
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http://bhxb.buaa.edu.cn//EN/     or     http://bhxb.buaa.edu.cn//EN/Y2013/V39/I3/320
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