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CSME 2022/02
Volume 43 No.1
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1-10
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Hypersonic Thermal Flow Past a Spherically Blunted Tangent-Ogive Nose Cone
Feng-Yao Changa and Huei Chu Wengb
aDepartment of Mechanical Engineering, Chung Yuan Christian University, Taoyuan 32023, Taiwan, ROC.
bDepartment of Mechanical Engineering, Chung Yuan Christian University, Taoyuan 32023, Taiwan, ROC.
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Abstract:
This study conducts a computational fluid dynamics (CFD) simulation to predict the thermal-flow fields and characteristics over a spherically blunted tangent-ogive nose cone at a Mach number of 6. The main objective is to analyze the influence of the bluntness ratio (BR) of the spherically blunted tangent-ogive nose cone on the shock wave, velocity, static pressure, static temperature, and density of the airflow around the nose cone under a fixed base radius, ogive radius, and hypersonic Mach number. The computational results reveal that the BR factor causes a change in shock wave type and shape, an increase in shockdetachment distance, and an increase in shock layerthickness, and an enhancement in shock wavestrength; furthermore, it makes the airflow static pressure, temperature, and density in the shock layerand on the blunted body surface generally increase, but makes the airflow velocity generally decrease.This study provides useful data for rockets, aircrafts, and reentry vehicles in hypersonic flight, especially the heat distribution of temperature, which involves the material selection and internal temperature control during flying-body design. By adjusting the bluntness ratio, it can be found that the maximum static temperature around the nose cone is 1,812.71 K at BR=0, and reaches 2,453.27 K at BR=1.
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Keywords: gas dynamics, high-speed flow, shock waves, heat transfer, spherical nose, tangent-ogive cone, bluntness ratio, detachment distance.
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*Corresponding author; e-mail:
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©
2022
CSME , ISSN 0257-9731
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