一种KFm低速翼型气动性能CFD评估
详细信息 查看官网全文
- 英文论文题名：Aerodynamic Performance Evaluation of a KFm Low Speed Airfoil
- 论文作者：杨勋平 ; 张利珍
- 英文论文作者：Xunping YANG ; Lizhen ZHANG ; AVIC Chengdu Aircraft Design & Research Institue
- 年：2016
- 作者机构：成都飞机设计研究所;
- 论文关键词：气动性能、CFD评估 ; 湍流模型、雷诺平均N-S方程
- 英文论文关键词：aerodynamic performance ; CFD evaluation ; SST ; RANS
- 会议召开时间：2016-09-04
- 会议录名称：2016海峡两岸流体力学研讨会论文摘要集
- 语种：中文
- 分类号：V224
- 学会代码：AGLU
- 会议名称：2016海峡两岸流体力学研讨会
- 会议地点：中国青海西宁
- 主办单位：中国力学学会
- 学会名称：中国力学学会
- 页数：1
- 文件大小：4690k
- 原文格式：D
- 会议级别：全国
摘要
为了获得一种低速模型飞机用翼型的气动性能,采用基于有限体积法的Fluent软件开展了9%厚度的KFm-2翼型CFD计算评估。通过求解基于k-ω的剪切应力传输湍流模型(SST)的雷诺平均N-S方程(RANS),评估了翼型气动性能,分析气流速度、后向台阶位置及高度参数改变对翼型性能的影响。结果显示KFm-2翼型的安定性好、失速迎角大(35°)、升阻比小,气流速度对升力线斜率和气动中心位置影响较小,台阶位置从50%弦长后移至70%增大了相同迎角的升力、提高升阻比,从4.5%弦长到6.1%台阶高度变化类似地增大相同迎角的升力、提高升阻比。说明台阶位置及高度参数对KFm-2翼型性能具有较大影响,适当台阶参数组合可改善气动性能。
The aerodynamic performance was evaluated of the airfoil on a low speed model aircraft. The computational code Fluent with finite volume method was used to analyze the airfoil KFm-2 of 9% thickness. The turbulence model based on k-ω shear stress turbulence model(SST) was selected when solving the Reynolds Averaged Navier-Stokes Equations(RANS).The results indicated that the KFm-2 airfoil had excellent moment and stall performance whereas small liftdrag ratio, and stall angle was about 35°. Airstream velocity had little influence on lift and aerodynamic center. Changing downstream step location from 50% to 70% chord improved the lift-drag performance and moment value, and step height had the similar effect when improved from 4.5% to 6.1% chord. Results indicated that location and height of step were important to airfoil KFm-2, and the aerodynamic performance might be improved by proper combination of step parameters.
The aerodynamic performance was evaluated of the airfoil on a low speed model aircraft. The computational code Fluent with finite volume method was used to analyze the airfoil KFm-2 of 9% thickness. The turbulence model based on k-ω shear stress turbulence model(SST) was selected when solving the Reynolds Averaged Navier-Stokes Equations(RANS).The results indicated that the KFm-2 airfoil had excellent moment and stall performance whereas small liftdrag ratio, and stall angle was about 35°. Airstream velocity had little influence on lift and aerodynamic center. Changing downstream step location from 50% to 70% chord improved the lift-drag performance and moment value, and step height had the similar effect when improved from 4.5% to 6.1% chord. Results indicated that location and height of step were important to airfoil KFm-2, and the aerodynamic performance might be improved by proper combination of step parameters.
引文