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采用Navier-Stokes方程与滚转运动方程耦合计算方法,比较研究了不同后掠角的双三角翼和翼身组合体的滚转运动特性,分析了机翼前缘后掠角及细长机身对非定常滚转力矩时滞环、动态流场结构和物面瞬时压力分布的影响。研究结果表明:主翼迎风面上的融合涡能量在80°/60°双三角翼上耗散较小,而在76°/40°双三角翼上耗散严重,这是造成两模型滚转力矩稳定性与时滞特性差异的主要因素;机身对气流的扰动作用,大幅增强了滚转力矩的线性分量;机身对气流的上洗作用,增强了边条涡与融合涡吸力及其时滞性,同时加剧了主翼背风面的两涡干扰;大滚转角时机身对横流流动的干扰,使得主翼背风面压力分布的时滞差异显著增加。该研究结果有助于认识后掠角与细长机身影响双三角翼滚转运动特性的物理机理。
The coupling motion between Navier-Stokes equation and roll motion equation is used to study the rolling characteristics of the double delta wing and wing body assembly with different sweep angles. The sweep angles of the leading edge and the slender fuselage Influence of Unsteady Rolling Moment on Hysteresis Ring, Dynamic Flow Field Structure and Surface Instantaneous Pressure Distribution. The results show that the energy of the convergent vortex on the windward side of the main wing dissipates less on the double delta wing at 80 ° / 60 ° and dissipates more on the double delta wing at 76 ° / 40 °, which results in two models of rolling moment Stability and delay characteristics of the main factors; the body of the disturbance to the air flow, a substantial increase in the rolling torque of the linear component of the fuselage on the air wash on the role of enhanced edge vortex and fusion vortex suction and the time Hysteresis, and exacerbated the vortex interference of the main wing leeward side; the interference of the fuselage body to the lateral flow at the large roll angle causes the time lag difference of the pressure distribution on the leeward side of the main wing to increase significantly. The results of this study will help to understand the physical mechanism of swept angle and slender body affecting the rolling motion of the double delta wing.