摘要
冲压发动机是导弹设计者关心的重要问题之一。在实际飞行中为了有效的跟踪和攻击目标,必然要面对带攻角的情况。为了更好的模拟弹体、进气道和掺混段一体化影响,本文采用二阶迎风隐式TVD格式,内外流分区耦合求解可压缩N S方程,数值模拟了掺混段出口压力与来流压力比为P P∞=4 2超临界状态下,二元方形截面"X"型布局一体化通气模型复杂流场。计算了不同攻角对冲压发动机性能和流场所产生的影响,并对结果进行了比较和分析。
The ramjet is one of the important questions, which the missile designers consider. In order to track and attack the aim effectively, the ramjet must meet the different attack-angles. In order to simulate the integrated effect of the complex inner and outer flow around the missile body, inlet and the firebox, the second order upwind implicit TVD schemes were used to solve the compressible N-S equations. The computational condition is Ma=2.2, P/P_∞= 4.2, under the super critical condition. And the configuration of the inlets is 'X' type with square section. The different attack-angles are calculated, and the effects of the attack-angles to the character and the flowfields of the ramjet were compared and analyzed in this paper.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2005年第1期99-103,共5页
Journal of Astronautics
关键词
内外流场
一体化布局
冲压发动机
数值模拟
Inner and outer flow
Integrated Configuration
Ramjet
Numerical Simulation
