CRM-WBPN风洞试验模型数值模拟

Numerical simulation of CRM-WBPN wind tunnel test model

基于雷诺平均Navier-Stokes(RANS)方程和多块对接结构网格技术,采用亚跨超CFD软件平台(TRIP 3.0),研究了共同研究模型(CRM)风洞模型支撑装置对CRM翼/身/架/舱(CRM-WBPN)模型压力分布及气动特性的影响。构造了一个包含小、粗、中、细网格的4套网格,并进行了网格收敛性研究,在升力系数为0.50条件下,开展了固定升力系数下模型支撑对CRM-WBPN模型和CRM-WB模型压力分布及挂架短舱阻力增量的影响,以及不同来流迎角下模型支撑对CRM-WBPN模型气动特性的影响。通过与NASA国家跨声速风洞设备(NTF)试验结果和CRM-WB模型数值模拟结果的对比分析,表明模型支撑对固定升力系数下挂架短舱阻力增量影响较小;在计算构型中考虑模型支撑的影响,引起升力系数和阻力系数下降、俯仰力矩系数增加,数值模拟结果更加接近相应的试验结果。

Based on the Reynolds-Averaged Navier-Stokes(RANS)equations and the structured grid(point to point)technology,the effects of support system on the aerodynamic characteristics of CRM Wing/Body/Pylon/Nacelle(CRM-WBPN)configuration are studied by using TRIP 3.0(Trisonic Platform version 3.0).A grid family,which includes a tiny,coarse,medium,and fine grid,is constructed,and grid convergence study is presented.The effect of support system on the drag increment between CRM-WBPN and CRM-WB model is discussed on lift coefficient 0.50.The influence of support system on the aerodynamic characteristics of CRM-WBPN is provided at different angles of attack.Compared with the experimental data from the NASA Langley National Transonic Facility(NTF)and the numerical results of the CRM-WB model,the present numerical results show that the support system has mild effect on the drag increment between WBPN and WB.The inclusion of support system into the computation model decreases the lift coefficient and drag coefficient,and increases the pitching moment coefficient.The numerical results of WBPNS model more closely match with the experimental results.