本文采用RANS(Reynold-Averaged Navier-Stokes)方法结合基于当地变量的转捩预测模型，针对某特殊布局形式的层流机翼验证机开展跨声速层流特性和参数敏感性分析。通过DLR F-5三维机翼构型对基于RANS的转捩预测方法进行算例验证分析，同时将某层流验证机中央翼段层流转捩预测结果与试验进行对比，证明了采用的计算方法完全适用于所研究问题。本文重点关注全机巡航状态附近的气动特性和中央验证段在不同飞行状态下的表面转捩位置及层流区长度。通过计算，进一步分析层流流动对全机升阻及力矩特性的影响。结果表明：马赫数、雷诺数、来流湍流度和迎角等均会对中央验证段表面转捩位置产生明显的影响，且影响规律差异较大。马赫数的增加会引起压力分布的较大变化，使转捩位置出现前后波动；雷诺数按同样幅度的递增会使得翼面转捩位置有规律的提前；而来流湍流度和迎角的增加会导致转捩提前，层流区长度明显缩小。
In this paper, the RANS (Reynold-Averaged Navier-Stokes) method combined with the transition model based on local variables is carried out on the transonic laminar flow characteristics and parameter sensitivity analy-sis for a special designed aircraft with laminar wing section. The RANS-based transition prediction method is vali-dated and analyzed by the transition prediction of the DLR F-5 three-dimensional wing. And the simulation results of the laminar wing section of the aircraft are compared with the corresponding experimental data. The pressure distribution and transition location on the upper surface both show good agreement with each other, and therefore further proves that the calculation method used in this paper is totally suitable for the problem. The present article mainly focuses on the aerodynamic characteristics of the whole aircraft in the cruise state, the transition location and the length of the laminar flow zone on the upper surface of the middle laminar wing section under different flight conditions. According to the calculation results, the influence of laminar flow on the lift、drag and moment characteristics of the whole aircraft are further analyzed. And the influence of key flow parameters such as Mach number, Reynolds number, freestream turbulence intensity and angle of attack on the transition position of the wing section surface were summarized. The results demonstrate that the transition position on the surface of the middle laminar wing section was impacted significantly by Mach number, Reynolds number, turbulence intensity and angle of attack of the free stream, but the influence rules are quite different. The increase of Mach number will cause a great change in the pressure distribution and make the transition position move forward and backward; The in-crease of Reynolds number by the same amplitude will make the transition position move forward regularly; And the increase in the turbulence intensity and angle of attack of the freestream will directly lead to the occurrence of an early transition, and the length of the laminar flow zone will be significantly reduced gradually.
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