摘要
该文以某中间有圆柱段的平流层飞艇为研究对象,在验证数值模拟方法的基础上,分析了尾翼、长细比、高度及雷诺数对飞艇气动阻力的影响。基于参数分析,采用TableCurve3D软件拟合给出了该艇型在水平姿态下的气动阻力系数估算公式,且给出攻角对公式的修正。研究表明:水平姿态下,平均风压系数沿着艇体头部逐渐减小,中间圆柱段保持稳定,沿着尾部逐渐增加;沿着艇体方向,风压系数曲线斜率拐点出现在各段连接附近。尾翼及艇体对阻力系数的贡献值随着俯仰角的增大而增加,但艇体是主要的贡献者;气动阻力系数随着长细比和高度的增加呈现先减小后增加趋势,随着Re数(1.0×10~7~2.0×10~8)的增加而递减。
A stratosphere airship with cylindrical sections in its middle was taken as a research object, the influence of fins, slenderness ratio, height and Re on aerodynamic drag force were studied by the verification of simulation method. Based on the parameter analysis, the estimating formula of aerodynamic drag coefficients under horizontal conditions was obtained using TableCurve3D software. What is more, a modified formula considering attack angles was also presented. The study demonstrates that mean wind-pressure coefficients decrease along the hull head, keep stable in the middle cylindrical section, and increase along the tail section. The curvature inflections of pressure-coefficients curves appear near the junctions of different sections. The contributive value of fins and hull to aerodynamic drag coefficients increases with the increase of attack angles, but hull is the main contributor. As the slenderness ratio or height increases, the aerodynamic drag coefficient decreases first and then increases. A decrease trend is presented with the increase of Re （1.0×107~2.0×108）.
出处
《工程力学》
EI
CSCD
北大核心
2017年第8期249-256,共8页
Engineering Mechanics
基金
国家自然科学基金项目(51678192)
