增升装置低速流动特性的雷诺数效应计算研究  

Numerical simulations of Reynolds number effect on flow characteristics at high-lift devices

作　　者：李中武[1] 梁益华[1] 

机构地区：[1]西安航空计算技术研究所第七研究室,陕西西安710019

出　　处：《飞行力学》2014年第1期10-14,共5页Flight Dynamics

基　　金：国家863计划资助(2012AA01A304)

摘　　要：通过求解RANS方程数值模拟了运输类飞机绕流流场,研究了从常规风洞试验至自由飞行范围雷诺数对增升装置上流动分离特性、压力分布及边界层转捩的影响。CFD结果预测的低速流动特性表明,随着雷诺数的增大,外襟翼上分离位置逐渐向后缘移动,吸力峰值变大,而增升装置前缘边界层转捩位置向前缘移动。与流动现象相对应,增升装置的升力系数逐渐增大,力矩系数变小,在雷诺数达到107量级时,升力系数及力矩系数的变化趋于平缓,而在6.0×106之前,增升装置的气动力对雷诺数影响十分敏感。Reynolds number effect on the flow separation and transition is investigated by solving N-S equation. The CFD results with Reynolds number 1.75 ×10^6-20. 0 ×10^6 are analyzed and some conclu- sions are given. The peak of suction is higher and the location of flow separation on outer flap is moving behind with the increase of Reynolds number. Meanwhile, the onset locations of laminar-to-turbulent transition moving forward. The aerodynamic force is enhanced markedly and the pitch moment is reduced obviously until 10^7scale. The aerodynamic force of the high lift device is very sensitive to the change of the Reynolds number.

关 键 词：增升装置 流动分离 雷诺数效应 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]