二元双喉道射流推力矢量喷管的数值模拟研究
A computational study of 2-D dual-throat fluidic thrust-vectoring nozzles
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摘要: 对二元双喉道射流推力矢量喷管的设计规律进行了数值模拟研究.结果表明,空腔长度、空腔扩张角、空腔收敛角、上游喉道高度等设计参数对喷管的推力系数、矢量效率以及内部流态均有着显著影响.研究中获得的较优的参数组合方案为:空腔长度2.61,空腔扩张角10°,空腔收敛角30°,上游喉道高度1.0,次流注入角150°(长度尺度以下游喉道高度无量纲化).当主流压比为4、次/主流压比为1.08、次流量为主流的2.5%时,该方案获得了14.34°的矢量角,且推力系数为0.967.Abstract: Numerical studies on 2-D dual-throat fluidic thrust-vectoring nozzles were performed to obtain the key design rules.Results show that length of primary nozzle cavity, divergent cavity ramp angle, convergent cavity ramp angle and height of upstream primary nozzle throat have great influence on thrust ratio, thrust vectoring efficiency and the internal flow patterns.The optimal package of parameters is: 2.61, 10°, 30°, 1.0 and 150°, respectively(the length scale is normalized by the height of downstream primary nozzle throat).This package can achieve a pitch thrust vector angle of 14.34° and a thrust ratio of 0.967 in the case of a primary flow pressure ratio 4, secondary/primary flow pressure ratio 1.08 and mass consumption of 2.5%.
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Key words:
- aerospace propulsion system /
- thrust-vectoring technique /
- nozzle /
- dual-throat /
- fluidic
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[1] Deere K A.Summary of fluidic thrust vectoring research conducted at NASA langley research center[R].AIAA-2003-3800,2003. [2] Deere K A,Berrier B L,Flamm J D,et al.Computational study of fluidic thrust vectoring using separation control in a nozzle[R].AIAA-2003-3803,2003. [3] Deere K A,Berrier B L,Flamm J D.A computational study of a new dual-throat fluidic thrust vectoring nozzle concept[R].AIAA-2005-3502,2005. [4] Flamm J D,Deere K A.Experimental study of a dual-throat fluidic thrust-vectoring nozzle concept[R].AIAA-2005-3503,2005. -
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