摘要
采用"亚跨超CFD软件平台"(TRIP)数值模拟了梯形翼全展长与半展长高升力构型的复杂流场,并与试验做了对比分析。对应风洞试验是在NASA Langley 14×22英尺亚声速风洞(FST)和NASA Ames 12英尺增压风洞(PWT)中完成的。计算中采用一方程SA湍流模型和MUSCL-ROE格式,并综合运用对接/重叠/拼接网格技术,数值模拟了两种高升力构型的气动特性,给出了典型站位的压力分布,并对比研究了不同结构网格技术对此类高升力构型的计算差异。研究表明,与修正后的试验数据相比,数值模拟得到的气动力系数和典型剖面的压力分布均与试验结果吻合良好。
With the help of TRIP solver in CFD platform, the trap wing full span and part span high-lift configurations have been numerical simulated included comparison with experimental results. Corresponding wind tunnel experiment achieved in NASA Langley 14）〈22 feet wind tunnel（FST） and NASA Ames 12 feet wind tunnel（PWT）. In this study, SA turbulence model and MUSCL-ROE scheme and patch/overlap/cross grid technology are applied. Computations on two kinds of high-lift configurations are performed to obtain their aerodynamic characteristic and Cp distribution on typical section, at the same time, comparison between different structured mesh methods is obtained also. The research results show that the numerical prediction of aerodynamic forces and Cp distribution in typical section is quite agreeable with experimental results.
出处
《空气动力学学报》
CSCD
北大核心
2013年第1期75-81,共7页
Acta Aerodynamica Sinica
基金
国家重点基础研究发展973计划(2009CB723801)
空气动力学国家重点实验室基金(SKLA2011A0106)
关键词
结构网格
高升力构型
气动特性
压力分布
structured mesh
high-lift configurations
aerodynamic characteristic
Cp distribution
