Hypersonic Intake Starting Characteristics–A CFD Validation Study
Hypersonic Intake Starting Characteristics–A CFD Validation Study
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DOI：
10.14429/dsj.62.1340
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发表时间：
2012-07
影响因子：
0.9
通讯作者：
S. Saha;D. Chakraborty
中科院分区：
文献类型：
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作者：
S. Saha;D. Chakraborty
对高超声速进气启动特性进行了数值模拟。使用商业计算流体动力学 (CFD) 软件求解三维 RANS 方程以及 SST 湍流模型。发现壁压分布和进气性能参数与3-8范围内不同自由流马赫数的实验数据吻合良好。进气的启动是由于质量捕获率的突然下降而导致的。壁面条件（绝热或等温）被认为对估计进气性能参数有显着影响。与等温条件相比，计算出的绝热条件下的未启动马赫数更高。对于未启动的情况，在进气口入口附近可以看到大的分离气泡，它负责将冲击系统从进气口排出。国防科学杂志，2012，62（1），第147-152页，DOI：http://dx.doi.org/10.14429/dsj.62.1340
Numerical simulation of hypersonic intake starting characteristics is presented. Three dimensional RANS equations are solved alongwith SST turbulence model using commercial computational fluid dynamics (CFD) software. Wall pressure distribution and intake performance parameters are found to match well with experimental data for different free stream Mach number in the range of 3-8. The unstarting of the intake is traced from the sudden drop of mass capture ratio. Wall condition (adiabatic or isothermal) is seen to have pronounced effect in estimating the performance parameters in the intake. The computed unstarting Mach number is seen to be higher for adiabatic condition compared to isothermal condition. For unstarting case, large separation bubble is seen near the entrance of the intake, which is responsible for expulsion of the shock system out of the intake. Defence Science Journal, 2012, 62(1), pp.147-152 , DOI:http://dx.doi.org/10.14429/dsj.62.1340