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|Title: ||The effect of the hypersonic bodies with aerospikes on drag reduction|
|Other Titles: ||伴隨氣尖裝置之極音速物體的減阻效應|
|Authors: ||劉晉銘;Liu, Chin-Min|
|Keywords: ||極音速;鈍體;氣尖;氣盤;減阻;k-ω紊流模組;克利金法;Hypersonic;Blunt body;Aerospike;Aerodisk;Drag reduction;k-ω Turbulence Model;Kriging Method|
|Issue Date: ||2017-08-24 23:52:35 (UTC+8)|
Orion MPCV (Multi-Purpose Crew Vehicle) is one of the state-of-the-art manned space vehicles nowadays which will engage in the deep space missions in the near future such as the journey to Mars and the asteroid landing. Besides, Orion spacecraft is a kind of blunt body, thus the phenomena concerning the high levels of pressure drag and aerodynamic heating are experienced during the atmospheric re-entry process.
Pressure drag and aeroheating stirred by the shock wave is the main challenge of hypersonic flight, and the blunt body is always the principle configuration at hypersonic flow regime for heat distribution, but it would induce tremendous drag to the body. Therefore, both aerospikes and aerodisks can be efficiently utilised as the approach for drag reduction purpose. Furthermore, the implication of drag and heat transfer reduction for the hypersonic bodies plays a crucial part in the future development of space science and technology.
In this thesis, we would research the effect of different geometric shapes of aerospikes with different disk gap widths on drag reduction. Accordingly, we implemented a series of Computational Fluid Dynamics (CFD) numerical simulation work via ANSYS Fluent CFD code to investigate and interpret the behaviour in relation to hypersonic flow over aerospiked blunt bodies. Moreover, the drag coefficient and the drag reduction efficiency of spiked blunt bodies would be worked on and acquired via Kriging-based optimisation method.
For the models we studied, we found that the drag on the spiked blunt bodies is much lower than the spike off one. The drag reduction efficiency especially would be predominated by the scale of recirculation zone, which increases as both the spike length and the gap size of aerodisk increase. Hence, the performance of drag diminution will depend on the design parameters of bodies such as main body configurations, aerospike length, tip geometric shapes and drag reduction schemes. The results from this research could be the cornerstone for the design of future hypersonic blunt bodies and space exploration vehicles.
|Appears in Collections:||[航空太空工程學系暨研究所] 學位論文|
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