一种翼身组合模型气动特性研究

 马震宇,侯迎欢,何中义

(郑州航空工业管理学院 航空工程学院,河南 郑州 450046)
摘要:基于一种后掠翼翼身组合体刚性模型,为研究其低速升阻力和俯仰力矩变化特性,进行低速风洞纵向测力实验,迎角α为-4°~+36°。根据模型实际实验状态,数值模拟其低速粘性绕流流场和升阻力特性,特征雷诺数为4×105。实验结果表明:在-4°~+15°迎角范围内,模型升力系数按明显线性关系增大;31°迎角时,升力系数获得最大值为1.15。36°迎角时,阻力系数值达最大为0.807。模型升阻力数值模拟结果与风洞实验值在计算攻角范围吻合良好,最大相对偏差11%,结合流场计算结果分析能够支持和综合分析风洞实验结果。
关键词:后掠翼模型;风洞实验;纵向气动力;低速流场;数值模拟
中图分类号:V211.7;V211.3 文献标志码:A doi:10.3969/j.issn.1006-0316.2018.05.006
文章编号:1006-0316 (2018) 05-0022-05
Aerodynamic Experiment and Numerical Simulation of a Backward Swept Wing Model
MA Zhenyu,HOU Yinghuan,HE Zhongyi 
( School of Aeronautical Engineering, Zhengzhou University of Aeronautics, Zhengzhou 450046, China )
Abstract:Based on a wing-body combination rigid model of backward swept wing, the longitudinal aerodynamic experiment was performed in a low speed wind tunnel to research the changing characteristics of the lift and drag and the pitching moment with the angle of attack α=-4°~+36°. According to experimental states of the model, numerical simulation of the flow field, lift and drag characteristics was implemented with the characteristic Reynolds number 4×105. The experimental results show that the lift coefficient of the test model changes linearly within α=-4°~+15°, the maximum of the lift coefficient is 1.15 at α=31°. The maximum of the drag coefficient is 0.807 at α=36°. The numerical simulation results are in good agreement with the wind tunnel test values within the calculation range of attack angle with maximum relative deviation 11%. The results,  combining with calculation and analysis of the low speed flow field parameters, are helpful to enrich and comprehensively analyze wind tunnel experiment results of the model.
Key words:backward swept wing model;wind tunnel experiment;longitudinal aerodynamic forces;low speed flow field;numerical simulation
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收稿日期:2017-11-02
基金项目:河南省高等学校重点科研项目计划(16A590001)
作者简介:马震宇(1964-),男,河南杞县人,工学硕士,研究员,主要研究方向为飞航器动力性能分析设计。
 

 

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