湍流模型对梯形翼高升力构型的影响  

The influence of turbulent models to trap wing simulation

作　　者：王运涛[1] 洪俊武[1] 孟德虹[1] 

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000

出　　处：《空气动力学学报》2013年第1期52-55,共4页Acta Aerodynamica Sinica

基　　金：国家重点基础研究发展计划;项目编号2009CB723800

摘　　要：采用"亚跨超CFD软件平台"(TRIP)数值模拟了梯形翼全展长高升力构型,主要目的是考察湍流模型对高升力构型气动特性的影响。相应的风洞试验是1998年在NASA Ames 12英尺增压风洞中完成的。本文采用一方程和两方程湍流模型,数值模拟了全展长高升力构型的气动特性并给出了典型站位的压力分布。研究表明,与修正后的试验数据相比较,在定常可收敛的迎角范围内,两种湍流模型得到的气动力系数和压力分布与试验结果吻合较好,SA一方程湍流模型的计算结果更接近试验值;迎角大于19.19°后,襟翼后缘的较大范围分离是导致采用SST模型不能得到收敛的气动特性的主要原因。The complex flow over trap wing is computed using CFD software TRIP（TRI sonic Platform）, the present study is part of TRIP validation effort for the capacity of numerical simulation of three-dimension high lift device. The corresponding test had been accomplished in NASA Ames 12＇ PWT in 1998, aerody- namic characteristics and pressure distribution were summarized. The SA turbulence models and ROE differ- ence scheme are adopted to simulate ＂full span＂ and ＂part span＂ high lift configurations, multi-grid technique and parallel technique are applied to accelerate convergence. The numerical aerodynamic characters are in good agreement with corrected experiment data before stall; for both configuration, the computed pressure distributions for the typical case are in good agreement.

关 键 词：TRIP 梯形翼 湍流模型 气动特性 压力分布 

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]