底部结构对飞行器阻力特性的影响

发布时间：2018-02-25 16:43

本文关键词： 底部流动超声速飞行器阻力特性　出处：《计算机仿真》2016年05期 　论文类型：期刊论文

【摘要】：为优化底部形状减小底部阻力,研究底部流场结构对超声速飞行器的阻力特性影响,采用计算流体动力学方法,建立了雷诺平均NS方程数值求解方法。通过与实验数据比较,验证了方法的可靠性,对含圆柱尾部、船尾的典型飞行器在不同马赫数和攻角下进行数值仿真。仿真结果表明:船尾设计具有减阻效果,且升阻比优于圆柱尾部。攻角变化对底部流场结构影响显著。飞行器的升力系数、阻力系数、升阻比及俯仰力矩系数,随攻角增加而增大。随马赫数增加,飞行器头部压力升高,底部压力降低,导致总阻力、底部阻力增大,然而,由于动压增大,使得相应的总阻力系数及底阻系数随之减小。计算分析为飞行器底部设计和优化提供了参考。
[Abstract]:In order to optimize the bottom shape to reduce the bottom drag, and to study the influence of the bottom flow field structure on the drag characteristics of the supersonic vehicle, a numerical solution method of Reynolds average NS equation is established by using the computational fluid dynamics (CFD) method, and the numerical solution method is compared with the experimental data. The reliability of the method is verified by numerical simulation of typical aircraft with cylindrical tail and stern under different Mach numbers and angles of attack. The simulation results show that the design of stern has the effect of reducing drag. The lift / drag ratio is better than the cylinder tail, and the change of attack angle has a significant effect on the structure of the bottom flow field. The lift coefficient, drag coefficient, lift resistance ratio and pitch torque coefficient of the aircraft increase with the increase of attack angle and increase with the increase of Mach number. The head pressure of the aircraft increases and the bottom pressure decreases, which results in the total resistance, the bottom resistance increasing, however, due to the increase of the dynamic pressure, The corresponding total drag coefficient and bottom resistance coefficient are reduced accordingly. The calculation and analysis provide a reference for aircraft bottom design and optimization.
【作者单位】：国防科学技术大学航天科学与工程学院;
【基金】：中国航天科技集团公司航天科技创新基金(CALT-16)
【分类号】：V211

【相似文献】