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提出一种上下错开的无尾联接翼,即前翼或者后翼上反一定角度,使得前后翼垂直方向的相对距离从翼根处开始到翼梢处逐渐增大,以达到减小前后翼气动干扰的目的,搭接的小翼具有翼梢小翼作用,可有效减小诱导阻力。采用基于RANS方程的数值方法,研究了前后翼分别上反10°,20°和30°时对总体气动特性的影响,结果表明,当前翼上反且上反角为30°时其联接翼系统气动性能最佳。对该联接翼布局在Ma=0.85,0.95和1.20下进行了数值分析,结果表明,其升力系数变化较小,阻力系数在Ma>0.85后才急剧增大,有应用于未来跨声速/超声速客机布局的潜力。
A kind of non-tail connecting wing which is staggered up and down is proposed, that is, the front wing or the rear wing is anti-fixed at an angle so that the relative distance between the front and rear wings in the vertical direction gradually increases from the wing root to the wing tip to reduce the aerodynamic The purpose of interference, overlapping winglets with wingtip effect, can effectively reduce the induced resistance. The numerical method based on the RANS equation is used to study the influence of the front and rear wings on the overall aerodynamic characteristics when they are respectively reversed 10 °, 20 ° and 30 °. The results show that the joint wing system Best aerodynamic performance. The results of numerical analysis of the coupling wing at Ma = 0.85, 0.95 and 1.20 show that the coefficient of variation of lift coefficient is small, and the drag coefficient increases sharply after Ma> 0.85. It has been applied to future trans / supersonic passenger aircraft Potential for layout.