摘要
使用自行发展的MFlow求解器对第六届AIAA阻力预测会议的翼身组合体外形进行了数值模拟研究。在文章中着重对比了线性涡黏模型和考虑二次本构关系的湍流模型的数值模拟结果,并与试验结果进行了比较。研究发现,考虑二次本构关系的湍流模型能够比较准确地预测翼身组合体的气动特性,而线性涡黏模型从迎角3.5°开始,高估了翼身结合处的分离流动,导致预测的气动力与试验结果差异较大。对翼身结合处局部流动和压力分布的详细分析,展示了两种模型预测的气动特性差别很大的原因。
Numerical investigations of the NASA Common Research Model from the 6th AIAA CFD Drag Prediction Workshop are performed with in-house solver MFlow.The results of linear viscosity model and nonlinear viscosity model with quadratic constitutive relation taken in to account are compared with experimental data.It is found that at angles-of-attack above 3.5 degrees,linear viscosity model over-estimates the separation at the corner of wing-body junction,therefore the results deviates from the experimental data.However,the turbulence model with Quadratic constitutive relation can improve the prediction of the secondary flow at the corner and leads to better agreement with experimental data.The causes of the difference between two models on the prediction are revealed through the analysis of local flow and pressure distribution at the corner.
作者
赵辉
张耀冰
陈江涛
马明生
ZHAO Hui;ZHANG Yaobing;CHEN Jangtao;MA Mingsheng(Computational Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China)
出处
《空气动力学学报》
CSCD
北大核心
2020年第5期901-907,I0002,共8页
Acta Aerodynamica Sinica
基金
国家数值风洞工程。
关键词
验证与确认
阻力预测
模型修正
二次本构关系
湍流模型
verification and validation
drag prediction
model correction
quadratic constitutive relation
turbulence models
