| 侧压式进气道与飞行器机体气动一体化设计及实验 |
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| 引用本文： | 范晓樯,李桦,易仕和,潘沙.侧压式进气道与飞行器机体气动一体化设计及实验[J].推进技术,2004,25(6):499-502. |
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| 作者姓名： | 范晓樯 李桦 易仕和 潘沙 |
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| 作者单位： | 国防科技大学,航天与材料工程学院,湖南,长沙,410073 |
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| 摘 要： | 以机体 推进系统耦合、三维侧压式进气道为基本特征,设计了采用超燃冲压发动机为推进系统的高超声速一体化冷流通气实验模型,在高超声速炮风洞中完成了飞行器的整体气动测力试验。在来流马赫数Ma=8.09的条件下,分别测定了飞行器结合单模块、3模块、5模块超燃冲压发动机在-4°～6°六个攻角下模型的气动力数据,并对实验结果作了分析。
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| 关 键 词： | 超音速冲压喷气发动机 进气道 飞行器 实验 |
| 文章编号： | 1001-4055(2004)06-0499-04 |
| 修稿时间： | 2003年10月20 |
Experiment of aerodynamic performance for hypersonicvehicle integrated with sidewall compression inlet |
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| FAN Xiao-qiang,LI Hu,YI Shi-he and PAN Sha.Experiment of aerodynamic performance for hypersonicvehicle integrated with sidewall compression inlet[J].Journal of Propulsion Technology,2004,25(6):499-502. |
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| Authors: | FAN Xiao-qiang LI Hu YI Shi-he and PAN Sha |
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| Institution: | Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China |
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| Abstract: | A hypersonic vehicle integrated with propulsion model is designed. Three dimension side compression inlet and scramjet were used. The aerodynamics force performance wind tunnel test of the model with none module, 1 module, 3 modules and 5 modules scramjet is finished in KD-01 hypersonic gun wind tunnel.Experimental data is measured when free Mach number is 8.09 and angle of attack is between -4° and 6°. The results were analyzed. |
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| Keywords: | Supersonic combustion ramjet engine Inlet Vehichle Experimentation |
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