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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