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Extended Far-field Composite Element Supersonic Wing-body Wave Drag Optimization Method
Received date: 2012-06-07
Revised date: 2012-08-16
Online published: 2012-08-23
The wave drag of a supersonic aircraft is closely related to its cross section area distribution, and a reasonable cross section area distribution is important to wave drag reduction. This paper presents a study of the fuselage shape parameterization based on the cross section area decomposition using the class-shape-transformation (CST), and proposes an extended far-field composite element (EFCE) wing-body wave drag optimization method, as well as a supersonic wing-body shape optimization case using the EFCE method, which yields a 39% reduction of the wave drag coefficient. It is suggested that the CST parameterization and the corresponding optimization process of the fuselage shape require fewer parameters and less computation cost than the wing; and similar to the area rule shape modification, the EFCE optimization code can automatically lead to a "coke bottle" fuselage shape.
GUAN Xiaohui , SONG Bifeng , LI Zhanke . Extended Far-field Composite Element Supersonic Wing-body Wave Drag Optimization Method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013 , 34(5) : 1036 -1045 . DOI: 10.7527/S1000-6893.2013.0192
[1] Zha G C, Im H, Espinal D. Toward zero sonic boom and high efficiency supersonic flight, part I: a novel concept of supersonic bi-directional flying wing. AIAA-2010-1013, 2010.
[2] Nikolic V, Jumper E J. Zero-lift wave drag calculation using supersonic area rule and its modifications. AIAA-2004-217, 2004.
[3] Kulfan B M, Bussoletti J E. "Fundamental" parametric geometry representations for aircraft component shapes. AIAA-2006-6948, 2006.
[4] Kulfan B M. New supersonic wing far-field composite-element wave-drag optimization method, "FCE". AIAA-2008-132, 2008.
[5] Lane A K, Marshall D D. A surface parameterization method for airfoil optimization and high lift 2D geometries utilizing the CST methodology. AIAA-2009-1461, 2009.
[6] Guan X H, Li Z K, Song B F. Exploring optimization of supersonic wing thickness distribution using FCE (Far-field Composite Element) method. Journal of Northwestern Polytechnical University, 2012, 30(2): 169-174. (in Chinese) 关晓辉, 李占科, 宋笔锋. 基于FCE方法的超声速机翼厚度分布优化. 西北工业大学学报, 2012, 30(2): 169-174.
[7] Kulfan B M. A universal parametric geometry representation method-"CST". AIAA-2007-62, 2007.
[8] Straathof M H, van Tooren M J L, Voskuijl M, et al. Aerodynamic shape parameterisation and optimisation of novel configurations. Proceedings of the RAeS Aerodynamic Shape Parameterisation and Optimisation of Novel Configurations Conference. London: Royal Aeronautical Soc., 2008: 1-14.
[9] Straathof M H, van Tooren M J L, Voskuijl M, et al. Development and implementation of a novel parametrization technique for multidisciplinary design initialization. AIAA-2010-3004, 2010.
[10] Straathof M H, van Tooren M J L. Extension to the class-shape-transformation method based on B-splines. AIAA Journal, 2011, 49(4): 780-790.
[11] Guan X H, Li Z K, Song B F. A study on CST aerodynamic shape parameterization method. Acta Aeronautica et Astronautica Sinica, 2012, 33(4): 625-633. (in Chinese) 关晓辉, 李占科, 宋笔锋. CST气动外形参数化方法研究. 航空学报, 2012, 33(4): 625-633.
[12] Kulfan B M. Recent extensions and applications of the "CST" universal parametric geometry representation method. AIAA-2007-7709, 2007.
[13] Jones R T. Theory of wing-body drag at supersonic speeds. NACA-RM-A53H18A, 1953.
[14] Chin W C. Supersonic wave-drag of planar singularity distributions. AIAA Journal, 1978, 16(5): 482-487.
[15] Jumper E J. Wave drag prediction using a simplified supersonic area rule. Journal of Aircraft, 1983, 20(10): 893-895.
[16] Bushgens G S. Aerodynamics, stability and controllability of supersonic aircraft. Guo Z, translated. Shanghai: Shanghai Jiao Tong University Press, 2009: 154-157.(in Chinese) Bushgens G S. 超声速飞机空气动力学和飞行力学. 郭桢, 译. 上海:上海交通大学出版社, 2009: 154-157.
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