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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。
In this paper, a stratospheric airship with a cylindrical section is taken as the research object. Based on the verification of the numerical simulation method, the effects of the tail, the slenderness ratio, the height and the Reynolds number on the aerodynamic drag of the airship are analyzed. Based on the parameter analysis, the formula of aerodynamic drag coefficient of the craft under horizontal attitude is given by TableCurve3D software fitting, and the correction of the formula of attack angle is given. The results show that in the horizontal attitude, the mean wind pressure coefficient decreases gradually along the hull head, the middle cylinder segment keeps stable and gradually increases along the tail. Along the hull direction, the slope inflection point of the wind pressure coefficient curve appears at each segment connection nearby. The contribution of tail and hull to drag coefficient increased with the increase of pitch angle, but hull body was the main contributor. The aerodynamic drag coefficient decreased first and then increased with slenderness ratio and height Re number (1.0 × 10 ~ 7 ~ 2.0 × 10 ~ 8) increase and decrease.