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| Aerodynamic Heating Reduction with Jet Array over Leading Edge of Hypersonic Vehicle |
| Received:July 03, 2018 Revised:November 25, 2018 |
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| DOI：10.7643/ issn.1672-9242.2018.11.006 |
| KeyWord:hypersonic flow jet leading edge aerodynamic heating heating reduction |
| Author | Institution |
| CHEN Hong-bo |
1. Research & Development Center of China Academy of Launch Vehicle Technology, Beijing , China |
| LI Xiao-yan |
1. Research & Development Center of China Academy of Launch Vehicle Technology, Beijing , China |
| HUANG Xi-yuan |
1. Research & Development Center of China Academy of Launch Vehicle Technology, Beijing , China |
| CHEN Zhi |
2. China Academy of Aerospace Aerodynamics, Beijing , China |
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| Abstract: |
| Objective To obtain the aerodynamic heating reduction mechanism over the leading edge for hypersonic vehicle. Methods A CFD study was carried out to research the rules of aerodynamic heating reduction with jet array over leading edge of hypersonic vehicle with a free-stream Mach number of 15, to determine the opening area of hypersonic flow. Holes for jet flow were set on the front wing edge of shock wave and rear wing section. Flow parameters were designed to simulate and calculate the flow field with ratio of total jet pressure and total incoming flow pressure between 0.002 and 0.02 to obtain regional flow field and surface heat flux features. Furthermore, the calculated results were compared and analyzed. Results With the increase of the total pressure ratio, 76%-99% of aerodynamic reduction was achieved at the jet impinged positions both in the shock interaction and wing tip rear regions. In the region of middle wind tip without jets, the heat flux was increased by 11%~24% with a total pressure ratio of 0.002; while the heat flux was decreased by 68%-86% with the increase of the total pressure ratio. It was also observed that the regional heat flux in front of the first jet orifice was amplified drastically above 2 times. Conclusion The aerodynamic heating reduction with jets is due to the jets injection which could push the high temperature gas far from the wall and lower the regional high heat flux. The zone of action for subsonic jet flow of total pressure ratio of low jet flow extends downstream only in a certain short distance, which would not generate higher heat flux at the attached point. While the high total pressure performs a sonic jet flow, it could be concluded that the heat reduction effects would be available in a long distance along the downstream region and the affected region would be enlarged by a higher total pressure ratio, which could produce a more obvious peak heat flux in the attached region simultaneously. |
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