Effect of Fineness Ratio on Hypersonic Thermal Flow past a Spherically Blunted Tangent-Ogive Nose Cone
Feng-Yao Changa, Yu-Chin Chienb and Huei Chu Wenga
aDepartment of Mechanical Engineering, Chung Yuan Christian University, Taoyuan 32023, Taiwan, ROC.
bDepartment of Intelligent Automation Engineering, National Chin-Yi University of Technology, Taichung 411030, Taiwan, ROC.
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Abstract:
In this study, a computational fluid dynamics(CFD) simulation is used to explore the external hypersonic thermal-flow fields and characteristics of a spherically blunted tangent-ogive nose cone. The main purpose is to analyze the influence of the fineness ratio (FR) of the nose cone on the shock wave, velocity, pressure, temperature, and density of the airflow, as well as the drag coefficient of the nose cone at a Mach number of 6 and a bluntness ratio of 5.The numerical results show that the effect of fineness ratio on the shock wave type, shape, and detachment distance is not apparent. In the area of the spherical nose, when the fineness ratio increases, the external airflow velocity increases, and the pressure,temperature, and density decrease, but the gradient values of velocity, pressure, temperature, and density remain unchanged. In the area of the tangent-ogive cone body, when the fineness ratio increases, theexternal airflow velocity also increases, and the pressure, temperature, and density also decrease;however, the gradient values of velocity, pressure,temperature, and density decrease significantly. With the increase of the fineness ratio, it can also be found that the drag coefficient of the spherically blunted tangent-ogive nose cone decreases. As FR=1, 2, and 3,the drag coefficients are 0.9082, 0.7586, and 0.7356,respectively. The results of this study can be applied to the design of the front part of a hypersonic flying object.
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Keywords: hypersonic gas dynamics, shock waves, heat transfer, flow drag, spherical nose, tangent-ogive cone, fineness ratio, detachment distance.
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