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跨音速条件下,大后掠飞翼布局翼身厚度分布影响激波/前缘涡干扰,进一步影响全机的失速特性.本文采用数值模拟方法,研究了跨音速时头部翼身厚度分布对小展弦比飞翼布局失速特性的影响规律及其对失速迎角附近激波/前缘涡干扰特性的影响.研究结果表明,减小机身头部厚度,将使机身背风侧第一道激波位置后移,激波/前缘涡干扰减弱,涡破裂点位置后移.将座舱位置后移10%机身长度,可使背风侧第一道激波位置后移到后缘附近,前缘涡破裂迎角增大4°左右,使全机失速迎角和可用升力系数增大,显著改善失速特性和俯仰力矩上仰特性.同时,将机头座舱位置后移,有利于减小全机的航向静不稳定裕度,提高航向静稳定性.该研究为大后掠飞翼布局气动布局设计和流动机理分析提供基础.
Under the condition of transonic speed, the wing thickness distribution of the large swept wing affects the shock / leading edge vortex disturbance, which further affects the stall characteristics of the whole machine.In this paper, the numerical simulation method is used to study the distribution of the wing body thickness The influence of small aspect ratio on the layout stall characteristics of the flying wing and its influence on the shock / front vortex interference characteristics near the stalling attack angle.The results show that reducing the thickness of the fuselage head will make the first After the position of the shock wave is shifted backward, the shock wave / leading edge vortex interference is weakened and the position of the vortex rupture point is shifted backward. When the position of the cockpit is shifted by 10% of the length of the fuselage, the position of the first shock on the leeward side can be moved back to the vicinity of the trailing edge , Leading edge vortex rupture angle of attack increased by about 4 °, so that the entire machine stall angle of attack and the available lift coefficient increases, significantly improve the stall characteristics and pitch moment Yang features.At the same time, the nose cockpit rearward position is conducive to reduce The stability of heading of the small complete machine is improved and the stability of heading is improved.The study provides the basis for the aerodynamic layout design and flow mechanism analysis of the large swept wing configuration.