摘要
进气道是冲压发动机设计中非常重要的环节,其入口设计会直接影响冲压发动机的总压恢复系数σ和流量系数φ等重要性能。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”型布局进气道、弹体和掺混段一体化通气模型复杂流场。计算比较了两种不同二元进气道入口形状流场和冲压发动机总压恢复系数σ、流量系数φ的结果,对其产生的原因进行了分析。
The inlet is the important factor for designing the ramjet, which directly affects the total pressure recovery coefficient σ and the flow coefficient φof the ramjet. The second-order upwind implicit TVD schemes were used to solve the compressible N-S equations for simulating the complex inner and outer flow fields about the 2D inlet, the missile body and firebox under the super critical condition, where the pressure ratio between the firebox exit and the free flow P/P∞=4.2. The configure of the inlets was ＂X＂ type with square section. The effects of the two types of the entries σ and φwere studied, and the reasons were analyzed in this paper.
出处
《计算力学学报》
EI
CAS
CSCD
北大核心
2006年第1期71-75,共5页
Chinese Journal of Computational Mechanics
基金
国家自然科学基金(10372036)
广东省自然科学基金(021197)资助项目
