为了更好地控制和规避飞机尾涡对飞行安全和机场运行效率的不利影响,本文重点研究近地尾涡的强度消散与涡核运动规律.使用 ANSYS中的DM模块建立 A320飞机机翼模型,并基于雷诺平均法(RANS)采用 RKE涡黏模型对雷诺应力项进行方程封闭,在天河一号超级计算机上采用多段拼接方法开展大尺度脱体尾涡数值模拟实验.基于实验数据分析了地面效应对涡核的下沉趋势和水平运动、涡间距、涡量及涡核速度等的影响,然后在尾涡流场中增加接地竖板,研究在机场跑道端设置人工干扰板时的尾涡运动和消散规律.结果表明,地表附面层能分离出二次涡,其缠绕于主涡周围诱发主涡加速消散并改变尾涡速度场的分布;人工干扰板能有效削弱尾涡的湍流动能,诱导主涡分离出二次涡系,触发涡系产生 Rayleigh-Ludwieg 相交不稳定性,加快主涡的下沉与迸裂,显著提高尾涡强度消散率.%In order to control and avoid the adverse influence of aircraft wake vortex on flight safety and airport efficiency,this study focused on wake vortex strength dissipation and vortex core movement in ground proximity.DM module of ANSYS was used to build the wing model of A320 aircraft.Based on Reynolds-averaged Navier-Stokes (RANS)method,RKE eddy viscosity model was applied to the equation closure of Reynolds stress term.Then a large scale numerical simulation of detached wake vortex using multi-segment stitching method was carried out via TH-1A supercomputer.To analyze the ground effects on wake vortex,the vortex core's vertical sinking,lateral movement,vortex space,vorticity and velocity were calculated according to the experimental data.Furthermore,a verti-cal plate-line was set in the flow field to study the influence mechanism of artificial intervention plates along the airfield runway on vortex dissipation and movement.The results indicate that secondary vortex can detach from ground surface boundary layer and wrap around the primary vortex,which may accelerate the vortex dissipation and lead to the redistribution of wake vortex velocity field.The plate-line can effectively weaken vortex turbulent kinetic energy,induce secondary vortex and trigger Rayleigh-Ludwieg instability.So the sinking and splitting of primary vortex are accelerated and vortex intensity decay is significantly enhanced.
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