一种边条三角翼布局的纵向特性数值模拟
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摘要
采用雷诺平均N-S方程(Reynolds-averaged Navier-Stokes,RANS),对一种边条三角翼布局进行CFD数值模拟,计算得到该布局的升阻特性、失速特性、纵向稳定性、纵向操纵性、前缘分离涡等情况。结果表明,该布局在小迎角范围内具有较为线性的升力曲线和力矩曲线,可通过线性拟合得到该机的气动力系数计算公式;超过一定迎角后,分离涡增升作用显著增强,升力线斜率增大,失速特性相比常规布局得到改善,但分离涡诱导的横向流动降低了升降舵效率。这种边条三角翼布局具有良好的气动特性,但应采用其它形式的舵面改善操纵性。
In order to study the longitudinal characteristics of an aircraft with strake-delta wing configuration, CFD numerical simulation is carried out based on Reynolds-averaged Navier-Stokes(RANS) equation. The lift-drag characteristics, stall characteristics, longitudinal stability and maneuverability, and leading edge detached vortex at high angle of attack of such a configuration are calculated. The results show that this configuration has a relatively linear lift-line and torque-line within a range of low angle of attack, and the aerodynamic coefficient formula can be obtained by linear fitting. While beyond this range, the lift-line slope increases significantly, and the stall characteristics are improved compared with the conventional configuration. However, the lateral flow induced by the detached vortex reduces the control efficiency of elevator. Such a strake-delta wing configuration has good aerodynamic characteristics, but more effective elevator should be used to improve the maneuverability in engineering applications.
In order to study the longitudinal characteristics of an aircraft with strake-delta wing configuration, CFD numerical simulation is carried out based on Reynolds-averaged Navier-Stokes(RANS) equation. The lift-drag characteristics, stall characteristics, longitudinal stability and maneuverability, and leading edge detached vortex at high angle of attack of such a configuration are calculated. The results show that this configuration has a relatively linear lift-line and torque-line within a range of low angle of attack, and the aerodynamic coefficient formula can be obtained by linear fitting. While beyond this range, the lift-line slope increases significantly, and the stall characteristics are improved compared with the conventional configuration. However, the lateral flow induced by the detached vortex reduces the control efficiency of elevator. Such a strake-delta wing configuration has good aerodynamic characteristics, but more effective elevator should be used to improve the maneuverability in engineering applications.
引文
[1]罗振谊,陈志敏,姚伟刚.不同雷诺数对钝前缘三角翼气动特性影响的研究[J].科学技术与工程, 2007, 7(7):1397-1401.
[2]全景阁,叶正寅,张伟伟.三角翼大迎角气动弹性研究[C]//第十二届全国空气弹性学术交流会会议论文集.中国空气动力学会:中国力学学会, 2011:477-482.
[3]张付昆,李栋.前缘钝度和雷诺数对三角翼流场的影响[J].科学技术与工程, 2013,13(16):4741-4746.
[4]Kroo I. Drag due to lift. Concepts for prediction and reduction[J].Annual Review of Fluid Mechanics, 2001,33(1):587-617.
[5]王云涛,张玉伦,王光学,等.三角翼布局气动特性及流动机理研究[J].空气动力学学报, 2013, 31(5):554-558.
[6]Chu J, Luckring J M. Experimental Surface Pressure Data Obtained on65-Degree Delta Wing Across Reynolds Number and Mach Number Ranges, Volume 3-Medium-Radius Leading Edge[J]. NASA Langley Technical Report Server, 1996, 7(2):431-448.
[7]杨小亮.双三角翼上分离及多涡流特性研究[D].长沙:国防科学技术大学. 2007
[8]孟宣市,乔志德,高超,等.低背鳍对细长平板三角翼大迎角空气动力的影响[J].航空学报, 2007, 28(3):545-549.
[9]吕鸿雁.三角翼大迎角绕流数值模拟的网格影响研究[C]//中国计算力学大会2014暨第三届钱令希计算力学奖颁奖大会论文集.中国力学学会计算力学专业委员会:中国力学学会, 2014:1-7.
[10]杨立芝,高正红.三角翼大迎角流场结构和气动力特性的数值分析研究[J].应用力学学报, 2004, 21(3):110-112+166.
[2]全景阁,叶正寅,张伟伟.三角翼大迎角气动弹性研究[C]//第十二届全国空气弹性学术交流会会议论文集.中国空气动力学会:中国力学学会, 2011:477-482.
[3]张付昆,李栋.前缘钝度和雷诺数对三角翼流场的影响[J].科学技术与工程, 2013,13(16):4741-4746.
[4]Kroo I. Drag due to lift. Concepts for prediction and reduction[J].Annual Review of Fluid Mechanics, 2001,33(1):587-617.
[5]王云涛,张玉伦,王光学,等.三角翼布局气动特性及流动机理研究[J].空气动力学学报, 2013, 31(5):554-558.
[6]Chu J, Luckring J M. Experimental Surface Pressure Data Obtained on65-Degree Delta Wing Across Reynolds Number and Mach Number Ranges, Volume 3-Medium-Radius Leading Edge[J]. NASA Langley Technical Report Server, 1996, 7(2):431-448.
[7]杨小亮.双三角翼上分离及多涡流特性研究[D].长沙:国防科学技术大学. 2007
[8]孟宣市,乔志德,高超,等.低背鳍对细长平板三角翼大迎角空气动力的影响[J].航空学报, 2007, 28(3):545-549.
[9]吕鸿雁.三角翼大迎角绕流数值模拟的网格影响研究[C]//中国计算力学大会2014暨第三届钱令希计算力学奖颁奖大会论文集.中国力学学会计算力学专业委员会:中国力学学会, 2014:1-7.
[10]杨立芝,高正红.三角翼大迎角流场结构和气动力特性的数值分析研究[J].应用力学学报, 2004, 21(3):110-112+166.