摘要
基于超声速双向飞翼构型,采用CFD方法进行阻力计算,采用F-BOOM程序进行声爆计算,研究翼型、平面形状和EFCE激波阻力优化算法对双向飞翼激波阻力和声爆的影响。计算结果表明,平底构型可以明显降低双向飞翼超声速客机的超声速巡航的声爆,却很大程度上增加了巡航阻力,而对称构型却恰好相反;细长的平面几何形状对降低双向飞翼激波阻力和声爆都有作用,尤其对降低对称构型的声爆效果明显;EFCE激波阻力优化算法对降低双向飞翼激波阻力有明显作用,但同时会带来声爆方面的不利影响。因此,超声速客机的减阻设计和低声爆设计需要进行权衡研究。
Based on SBiDir-FW （ supersonic bi-directional flying wing ） , CFD （ Computational Fluid Dynamics ） method is used to calculate the drag and F-BOOM method is applied to compute the sonic boom;this study focuses on how the airfoil, flat shape and EFCE shock wave drag optimization algorithm affect the drag and sonic boom of SBiDir-FW. The results and their analysis show preliminarily that： （ 1 ） flat bottom configuration can reduce the cruise sonic boom of SBiDir-FW remarkably, but it greatly increases the cruising drag, while the opposite phenome-non can be detected in symmetrical configuration;（2）slender flat shape can reduce drag and sonic boom of SBiDir-FW, especially for reducing the sonic boom of symmetrical configuration;（3）EFCE shock wave drag optimization algorithm can reduce the shock wave drag of SBiDir-FW obviously, but will also bring adversely effect on sonic boom. Therefore, the balance should be weighed when considering the design of low drag and low sonic boom for supersonic aircraft.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2014年第4期517-522,共6页
Journal of Northwestern Polytechnical University
关键词
超声速客机
双向飞翼
激波阻力
声爆
aerodynamic configurations, aerodynamic drag, algorithms, airfoils, angle of attack, calculations,computational fluid dynamics, design, Euler equations, flow fields, Lagrange multipliers, Mach number, mesh generation, optimization, pressure, schematic diagrams, shock waves, supersonic air-craft, wings
bidirectional flying wing, shock wave drag, sonic boom
