大型客机低速构型高雷诺数风洞腹撑支架干扰数值模拟

风洞到飞行相关性修正是获取现代大型客机低速气动特性的重要手段，通常采用增压提高风洞试验雷诺数，而支架干扰修正是该修正体系的一个关键环节。采用数值模拟研究了增压风洞腹撑的支架干扰，并分析了腹撑对飞机各部件的干扰及其对风洞流场的影响。通过数值模拟与风洞试验对比，表明升力系数相差0.006，阻力系数最大相差0.001 2，俯仰力矩系数最大相差0.01，验证了CFD数值模拟方法的可靠性。CFD计算结果表明：腹撑使得全机升力增加、阻力减小，俯仰力矩增加；腹撑对升力影响的主要部件是机翼，腹撑使得风洞中心以上动压增加，提升上翼面流速，从而增加了机翼的升力；与传统认识不同的是腹撑对阻力影响为负，且主要影响部件为缝翼，原因为缝翼下偏使得法矢分量向前从而减小了阻力；腹撑对俯仰力矩影响的主要部件是机身及平尾。研究结果揭示了腹撑对飞机气动特性影响的量级、主要影响部件及其流场变化，可为支架干扰数据修正及支架优化设计提供参考。所得结论可更好用于支架干扰试验的开展及风洞到飞行数据的修正，具有一定的工程实用性。

Numerical simulation of ventral sting interference in high Reynolds number wind tunnel for civil aircraft low speed configuration

The wind tunnel to flight correlation correction is an important means to obtain the low-speed aerodynamic characteristics of modern civil aircraft. The method of increasing the wind tunnel test pressure is usually used to improve the Reynolds number, and the sting interference correction is a key part of the correction system. The numerical simulation is used to study the sting interference of the pressurized wind tunnel, and the variation of flow field and the main affected parts are analyzed. The comparison of the numerical simulation with the wind tunnel test shows that the lift coefficient differs by 0.006, the drag coefficient has a maximum difference of 0.001 2, and the pitching moment coefficient has a maximum difference of 0.01, verifying the reliability of the CFD numerical simulation method. The CFD simulation results show that the ventral sting increases the lift of the whole aircraft, reduces the drag, and increases the pitching moment. The ventral sting has a major influence on the lift of the wing. The ventral sting increases the dynamic pressure above the center of the wind tunnel and increases the flow velocity of the upper surface of the wing, thereby increasing the lift of the wing. Different from the traditional understanding, the ventral sting has a negative influence on the drag, and the main affected parts are slats because the deflection of the slats makes the normal vector part forward and reduces the drag. The main affected parts of the ventral sting on pitching moment are the fuselage and the horizontal tail. The results reveal the magnitude of the ventral sting on the aerodynamic characteristics, mainly affected parts, and the variation of flow fields. The results can provide reference for the correction of the sting interference and the optimization design of the support. The conclusion can be better used in the wind tunnel sting interference test and wind tunnel to flight data correction with certain engineering practicability.