二元喷管流体矢量控制方案数值研究

张相毅; 王如根; 徐学邈; 周敏

二元喷管流体矢量控制方案数值研究

空军工程大学工程学院, 西安 710038

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出版历程
- 收稿日期: 2006-09-04
- 修回日期: 2007-01-09
- 刊出日期: 2007-09-28

Computational analysis of fluidic vector control concepts for binary nozzle

The Engineering Institute, Air Force Engineering University, Xi'an 710038, China

摘要

摘要: 采用基于雷诺平均的三维N-S方程和RNGk-ε湍流模型对两种流体注入方式下的某型二元收敛-扩散喷管全流场进行了数值模拟.计算结果表明:在激波诱导和喉道倾斜矢量控制方案下, 扩散段射流位置对喷管矢量效率的影响趋势是一致的, 射流位置越靠近喷口, 喷管获得的矢量角越大.相同射流流量在同一位置注入时, 由于喉道倾斜方案下的喷管主流可以实现亚声速偏转, 所以其总压损失较激波诱导方案要小.
- 航空、航天推进系统 /
- 喉道倾斜 /
- 激波诱导 /
- 射流位置 /
- 推力矢量
Abstract: The full-flow field of a certain 2DCDN(2-dimensional convergence-diffusion nozzle) with two fluidic thrust vectoring concepts was simulated numerically by using 3D Reynolds average N-S equation and RNG k-ε turbulence model.The calculated results show that,the effect of flap injector position on the nozzle vectoring efficiency is consistent under shock vector control and fluidic throat skewing package.The bigger vector angle could be obtained as the injector position approaches the nozzle outlet.When the same jet flux is injected from the same position,the total pressure loss of throat skewing concept is less than that of shock vector control concept,since the main nozzle under throat skewing concept can achieve subsonic turning.
- aerospace propulsion system /
- fluidic throat skewing /
- shock vector control /
- injector position /
- thrust vectoring

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参考文献(6)

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