高超声速球锥形弹箭气动热边界层转捩的数值计算和研究
首发时间:2009-04-02
摘要:采用工程算法与数值计算相结合的方法,求解定常流动边界层为层流和湍流时,高超声速(马赫数5-8)条件下,球锥形弹箭头部的气动热。选择费-里德尔(Fay/Riddle)公式计算头部驻点热流通量;李斯(Lees)公式计算外表面热流通量;巴特(Batt)转捩准则确定边界层层流与湍流的转捩点。将其作为第三类边界条件线性化,在非结构化网格上用有限容积法,进行球锥形弹箭头部,在无热防护和热屏蔽情况下的温度场数值计算。分析比较有转捩和无转捩时,球锥形弹箭头部的温度分布差异,为弹箭头部热防护提供有益的参考和依据。
关键词: 弹箭气动热 费-里德尔方法(Fay/Riddle) 李斯方法(Lees) 巴特准则(Batt)
For information in English, please click here
Researching and Calculating Steady Super/Hypersonic Viscous Flow for Aeroheating of the Semi-sphere Cone Missile Head
Abstract:The engineering method and numerical simulation were combined to solve the super/hypersonic aerodynamic heating of the semi-sphere cone missile head at laminar flow and turbulent flow boundary layer of steady state flow. Fay/Riddle formula, Lee’s method and turbulent heating-rate expression are applied in the computation for the heat-flux of missile head and these formulas are linearized as the third kind boundary condition. Batt’s transition criteria, the unstructured grid and the finite volume method are adopted to calculate the temperature distribution of the missile’s head with no heat protection system, and then analyze the influence caused by the turbulent heat transfer. The results can provide the useful reference for the heat protection of missile’s head.
Keywords: Aeroheating of missile Fay/Riddle’s formula Lees’formula Batt’s transition criteria
基金:
论文图表:
引用
No.3102715805712386****
同行评议
共计0人参与
勘误表
高超声速球锥形弹箭气动热边界层转捩的数值计算和研究
评论
全部评论0/1000