Dimensionless analysis of the unstart boundary for 2D mixed hypersonic inlets
Dimensionless analysis of the unstart boundary for 2D mixed hypersonic inlets
复制标题
DOI：
10.1017/s0001924000002505
复制
发表时间：
2008-09
期刊：
影响因子：
--
通讯作者：
J. Chang;D. Yu;W. Bao;L. Qu
中科院分区：
文献类型：
--
作者：
J. Chang;D. Yu;W. Bao;L. Qu
进气道不起动边界是高超声速进气道的重要问题之一，也是超燃冲压发动机保护控制的基础。针对这一问题，采用雷诺平均（RANS）方法，采用RNG（Renormalisation Group）k-ε湍流模型，对不同自由度和背压条件下的二维内外压混合进气道的二维定常流场进行了数值模拟，并对两种不同的进气道不起动现象进行了分析。本文基于“数值试验”数据，采用量纲分析方法寻找描述进气道不起动边界的本质变量。分别对前体和隔离段的无因次压比进行了分析。结果表明，二元混合式高超声速进气道的不起动边界由M0、α和Re 0决定。压比π随M0的增大而增大，随α的增大先增大后减小。压比π随Re 0的增大而增大。Re 0（Re 0 2× 10 7）对π的影响很小。
Abstract Inlet unstart boundary is one of the most important issues of the hypersonic inlet and is also the foundation of the protection control of a scramjet. To solve this problem, the 2D internal steady flow of a 2D mixed internal/external compression hypersonic inlet was numerically simulated at different freestream conditions and backpressures with a RANS (Reynolds-Averaged Navier-Stokes) solver using a RNG (Renormalisation Group) k-ε turbulence model, and two different inlet unstart phenomena were analysed. The dimensional analysis method was introduced to find the essence variables describing the inlet unstart boundary based on “numerical experimental” data in this paper. The dimensionless pressure ratios of the forebody and isolator were analysed respectively. The results show that the unstart boundary of the 2D mixed hypersonic inlet is determined by M0, α and Re0. Pressure ratio π increases with M0 increasing, and it increases firstly and decreases then with α increasing. Pressure ratio π increases with Re0 increasing. Re0 (Re0 2×107) has little effect on π.