激波诱导二元矢量喷管内流特性数值研究

Computational analysis on static internal flow field of shock vector controlled vectoring exhaust nozzles

School.of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要: 采用三种不同湍流模型分别对激波诱导二元矢量喷管内流场进行计算,并将计算结果与模型试验结果进行了分析比较,得出重整化群(RNG)k-ε二方程模型为文中数值模拟中最有效的湍流模型。对该型喷管的计算结果分析表明,喷管矢量角的计算值和实验值基本吻合;在NPR=4,ω=9.6%情况下,矢量角最大可以达到16.61°;注气位置、注气压力和喷管落压比对矢量角的影响比较大。
- 航空、航天推进系统 /
- 湍流模型 /
- 矢量喷管 /
- 内流特性 /
- 数值模拟
Abstract: After comparing the results of three different turbulence models in computing static internal flow field of shock vector controlled vectoring exhaust nozzles by means of second order upwind schemes,(RNG) k-turbulence model shows to be the most valid turbulence model,and the computation results have been compared with that of the scaled model experiments.The results indicate that small nozzle pressure ratio and large inject mass flow rate will result in a larger vector angle.
- aerospace propulsion system /
- turbulence model /
- vectoring nozzles /
- flow characteristics /
- numerical simulation

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