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翼弦格宽比对栅格翼组合体气动特性影响的数值研究

发表时间:2011-06-30  浏览量:1580  下载量:669
全部作者: 邓帆,陈少松,陶钢,谭献忠
作者单位: 南京理工大学能源与动力工程学院
摘 要: 为寻求亚跨声速和低超声速阶段内栅格翼的最佳翼弦格宽比,首先用风洞试验的方法得出其中1个翼弦格宽比栅格翼滑翔增程弹的气动数据,并与数值模拟的结果相比较,验证数值计算中网格生成的有效性;然后对4种不同翼弦格宽比的栅格翼组合体在所研究速度范围内的气动特性进行数值模拟。结果显示:亚跨声速和低超声速阶段翼弦格宽比在1�2左右时的栅格翼气动特性最好,为进行提高栅格翼滑翔增程弹气动特性的风洞研究提供了参考。
关 键 词: 航天器结构与设计;翼弦格宽比;栅格翼;风洞试验;数值计算
Title: CFD investigations on the influence of chord�to�width ratio on aerodynamic characteristics of grid fin�body configurations
Author: DENG Fan, CHEN Shaosong, TAO Gang, TAN Xianzhong
Organization: School of Energy and Power Engineering, Nanjing University of Science and Technology
Abstract: In order to research the aerodynamic characteristics of grid fins influenced by chord�to width ratio at subsonic/transonic speeds and supersonic speeds, a grid fin�body configurations was adopted in wind tunnel test, compared with its data of numerical calculation, the results proved the effectiveness of grid generating, then investigated on the influence of four different chord�to�width ratios brought to aerodynamic characteristics of grid fin�body configurations by the method of numerical calculation. The results indicated that there was a chord�to�width ratio of optimal aerodynamic characteristics at subsonic/transonic speeds and supersonic speeds, and this number was around 1.2, which provided useful information for the wind tunnel investigation about glide long�range missile with grid fins.
Key words: spacecraft structure and design; chord�to�width ratio; grid fins; wind tunnel test; numerical calculation
发表期数: 2011年6月第12期
引用格式: 邓帆,陈少松,陶钢,等. 翼弦格宽比对栅格翼组合体气动特性影响的数值研究[J]. 中国科技论文在线精品论文,2011,4(12):1059-1063.
 
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