基于涡流发生器的风洞侧壁附面层控制

刘光远; 王瑞波; 邓吉龙; 陈宏涛

doi:10.13224/j.cnki.jasp.2016.09.012

基于涡流发生器的风洞侧壁附面层控制

doi: 10.13224/j.cnki.jasp.2016.09.012

中国空气动力研究与发展中心高速空气动力研究所, 四川绵阳 621000

详细信息

作者简介:
刘光远(1983-),男,山东曹县人,工程师,硕士,主要从事跨声速试验空气动力学研究.

中图分类号: V211.7
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出版历程
- 收稿日期: 2015-02-05
- 刊出日期: 2016-09-28

Wind tunnel side wall boundary layer control based on vortex generator

High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 为降低风洞侧壁附面层对半模型数据的影响，在前期数值模拟的基础上，研制了一种适用于2.4m跨声速风洞半模型试验段侧壁的梯形涡流发生器，并进行了试验验证.结果表明：加装涡流发生器效果明显，亚声速范围内能够使附面层厚度降低20%~30%，对主气流均匀性影响可忽略；加装后半模型零升阻力系数降低，升力线斜率增大，压力中心向机身移动，体现了明显的附面层减薄效果，证明所研制的涡流发生器可应用于亚声速半模型试验中.
- 风洞 /
- 涡流发生器 /
- 附面层厚度 /
- 半模型试验 /
- 流动控制
Abstract: Combined with former numerical simulating results, vortex generators applicable for 2.4m transonic wind tunnel half-model test section were designed and validated to reduce side wall boundary layer effect. Results show that 20%-30% boundary layer thickness is reduced using trapezia-shaped flat vortex generators in subsonic conditions, and the influence on flow field uniformity is neglectable. The decrease of zero-lift drag and increase of lift-slope are found after vortex generators installation, meanwhile pressure center moves toward fuselage. Both trends are distinct evidence of thinner boundary layers. The developed vortex generators can be applied to half-model tests for subsonic conditions.
- wind tunnel /
- vortex generator /
- boundary layer thickness /
- half-model test /
- flow control

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参考文献(18)

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