CAJ | 학술논문

民机低速增升装置失速特性是具有挑战性的空气动力学难题之一，决定着飞机起、降阶段机翼处于流动分离或尾迹干扰状态时的操纵稳定性，是气动设计必须关注的重要方面。利用基于N-S方程的自研多块结构网格计算软件和混合网格计算软件，对NASA高升力梯形机翼标准模型开展了失速特性计算研究，系统评估了计算软件、计算网格、湍流模型等主要因素对失速特性的影响，获得了有效预测高升力构型失速特性的计算方案，并将其成功应用于工程实际，为增升装置失速特性计算评估提供了有意义的参考。
민궤저속증승장치실속특성시구유도전성적공기동역학난제지일，결정착비궤기、강계단궤익처우류동분리혹미적간우상태시적조종은정성，시기동설계필수관주적중요방면。이용기우N-S방정적자연다괴결구망격계산연건화혼합망격계산연건，대NASA고승력제형궤익표준모형개전료실속특성계산연구，계통평고료계산연건、계산망격、단류모형등주요인소대실속특성적영향，획득료유효예측고승력구형실속특성적계산방안，병장기성공응용우공정실제，위증승장치실속특성계산평고제공료유의의적삼고。
Stall characteristic of civil aircraft low-speed high-lift device is one of the challenging aerody-namics problems .It determines the control stability of wing in the flow separation or wake interference state when airplane is taking off and landing .It is an important aspect that aerodynamic design must be paying attention to .In this paper ,CFD computational study is performed on the standard model of NASA high-lift trapezoidal wing by using our in-house multi-block structured mesh solver and unstructured mesh solver based on RANS equation .Predictive capabilities for stall characteristic from solvers ,meshes and turbulence models are systematically evaluated .Calculation scheme which can effectively predict stall characteristic of high-lift configurations is obtained and it was applied in practical engineering successful-ly .The aim is to provide a meaningful guideline for stall characteristic prediction of civil aircraft high-lift system .