攻角下高速弹头气动热的数值研究
毕业论文关键词 高速弹头 气动热 边界层转捩 数值计算
Title Research of the Numerical Calculation of Aerodynamic Heating over Projectile’s Head at High Speed under Angle of Attack
Abstract
The prediction for the aerodynamic heat of high-speed flight has always been the
focus of military science research in all countries. Through the combination of
engineering algorithms and numerical simulation, this paper made a prediction on
the aerodynamic heating environment and internal temperature distribution for
the projectile's head at high speed flying at zero angle of attack under different mach
numbers.
A two-dimensional model was applied for the projectile's head, whose surface was
pided into four parts: stationary point, hemispherical portion, cone body and the
round face of tapered cone body. For the first three parts, engineering calculation
was carried out to give the third boundary condition, and it gave the first boundary
condition for the last part. Combined with the heat transfer program, the paper
applied a numerical calculation for the transfer of inner heat within the projectile's
head, and obtained the final results for prediction.
As for the transition of boundary layers, the paper made a comparison between the
calculation result only counting the laminar flow and the result counting the
turbulent conditions, thus showing the impact of boundary layer transition on the
aerodynamic heating env-
ironment and internal temperature distribution faced by the projectile's head at high speed.
Keywords the projectile's head at high speed, Aerodynamic Heating, the transition of boundary layers, numerical calculation
目 次
1绪论 .. 1
1.1 研究背景及意义.. 1
1.2 国内外研究现状.. 2
1.3 本文的主要工作.. 5
2弹头各条边上的热流密度计算及热传导计算程序 7
2.1 高速弹头驻点处热流密度计算 . 8
2.2 高速弹头球头表面的传热计算 . 9
2.3 高速弹头锥面的传热计算 . 10
2.4 平板绕流的传热计算 .. 12
2.5 圆锥绕流的传热计算 .. 14
2.6 高速弹头边界层转捩区的传热计算 .. 16
2.7 热传导计算程序 17
2.8 本章小结 18
3弹头建模及数值计算结果分析 19
3.1 弹头形状及各项参数 .. 19
3.2 数值计算结果及分析 .. 20
3.3 本章小结 39
结论 40
致谢 41
参考文献.. 42
图2.1 零攻角下球锥形弹头各部位热流密度示意 . 8
上一篇：微通道内沸腾换热强化传热特性研究