HiLiftPW-3高升力构型数值模拟

基于雷诺平均Navier-Stokes方程和拼接网格技术，采用MUSCL-Roe格式和Spalart-Almaras一方程湍流模型，对第3届高升力构型性能预测会议提供的两组高升力标模进行了数值模拟，主要目的是确认本文计算方法模拟复杂高升力构型的能力。研究内容主要包括高升力构型网格生成技术、网格收敛性研究及气动特性数值模拟。通过与JAXA （Japan Aerospace eXploration Agency）提供的测压、测力试验结果的对比分析，表明，在失速迎角之前，数值模拟得到的气动力系数和压力分布均与试验结果吻合；较好地模拟了局部外形变化引起的气动特性差量。本文建立的数值模拟方法对典型运输机三段翼布局的低速问题具有良好的适用性，可以为大飞机低速构型的气动设计及评估提供技术支撑。

Numerical simulation of high-lift configuration from HiLiftPW-3

Based on the Reynolds-averaged Navier-Stokes equations and cross-grid technology, this paper adopts the second-order MUSCL-Roe scheme and SA turbulence model to simulate two kinds of high-lift configurations from HiLiftPW-3. To validate the paper's numerical methods, the grid-convergence and aerodynamic characters for high-lift configuration are simulated. The comparison with the experimental data of pressure and aerodynamic force from JAXA (Japan Aerospace eXploration Agency) shows that, before reaching the stall angle, the aerodynamic coefficients of the numerical simulation and Cp distribution are highly anastomosed with the experimental data, providing a preferable simulation of the aerodynamic characters of dispersion from the variation of local configurations. The paper's numerical methods are well applicable to the typical high-lift configuration and could provide technological support for the aerodynamic design of civil plane in low-speed configuration.