线性塞式喷管外流干扰数值计算与冷流试验

程诚; 王一白; 刘宇

线性塞式喷管外流干扰数值计算与冷流试验

北京航空航天大学宇航学院, 北京 100191

基金项目: 航天支撑技术基金(0476002)

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出版历程
- 收稿日期: 2011-05-02
- 修回日期: 2011-12-30
- 刊出日期: 2012-04-28

Numerical simulation and cold-flow test of outflow effect on linear aerospike nozzle

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 采用有限体积法对由塞锥截短率为25%的线性塞式喷管和升力体构成的塞式喷管运载器风洞冷流试验模型进行仿真计算,并结合试验测量结果,研究了不同高度(压比)下外流对线性塞式喷管流场结构和性能的影响.结果表明,外流干扰导致线性塞式喷管内流过膨胀和横向侧流强度增加,并影响塞锥底部气流的受限流动;低空工况下外流的存在造成塞锥壁面和底部压强降低以及运载器底部阻力增加,喷管性能损失较大;高空工况下塞锥壁面和底部的压强已经不再受外流的影响,喷管性能损失较小,主要由运载器底部阻力损失造成.
- 塞式喷管 /
- 外流干扰 /
- 性能损失 /
- 数值模拟 /
- 冷流试验
Abstract: Finite volume method was adopted to get the simulation results of aerospike nozzle vehicle model for cold-flow test in wind tunnel which was composed of a linear plug nozzle truncated rate 25% and a lift body.Simultaneously combined with test measurements,outflow effect on flow field structure and performance of linear plug nozzle at different heights (pressure ratio) were presented.It is shown that outflow interference results in excessive expansion of jet and increase of the intensity of lateral flow in linear aerospike nozzle,and also affect the restricted flow around plug bottom.Under the low-altitude flight conditions,there is a serious loss of nozzle performance caused by pressure decrease on plug wall and at the bottom,and a vehicle base drag increase due to the existence of outflow.Under high-altitude flight conditions,the loss of nozzle performance mainly caused by vehicle base drag loss is small,because the pressure on plug wall and at the bottom is no longer affected by outflow.
- aerospike nozzle /
- outflow interference /
- performance loss /
- numerical simulation /
- cold flow test

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参考文献(12)

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