Prediction of supersonic flow over compression corner

被引：1
作者：
Sidik N.A.C. [1 ]
Loon K.W. [1 ]
机构：
[1] Department of Thermo Fluid, Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 UTM Skudai, Johor
来源：
Journal of Applied Sciences | 2011年 / 11卷 / 19期
关键词：
Compression corner; Finite difference; FLUENT; Shock wave; Supersonic flow;
D O I：
10.3923/jas.2011.3397.3404
中图分类号：
学科分类号：
摘要：
Numerical investigation of supersonic flow over two-dimensional compression corner. The laminar viscous and inviscid flow equations were discretised using finite different technique and the computer program code was developed using MATLAB. The analysis was conducted for corner angles of 5 to 20° and the flow velocity was varied from 2.5 to Mach 3.5. In the current study, we found that the magnitudes of peak pressure and recirculation region on the ramp were significantly affected by the flow velocity and corner angles. Results obtained were validated by using analytical solutions as well as from previous researchers and they are found to be in good agreement. © 2011 Asian Network for Scientific Information.
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页码：3397 / 3404
页数：7
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