摘要
为了简化燃烧室流场模拟,提高内外流场数值仿真效率,为高超声速飞行器一体化构型提供设计依据和参考,发展了一种在流动控制方程组中加入源项的数值模拟方法。通过调节源项作用位置及大小,该方法可实现对超燃冲压发动机燃烧室内的添质添能流动的模拟。与直联式试车台实验数据对比表明,该方法能够较好地模拟冲压发动机内压力分布,能够满足飞行器气动/推进一体化构型方案设计及总体方案设计阶段的需求。
A source ternl nlethod is developed to simulate tile flow field of scranljet conlbustion chanlber. By configuring the value and adding position of the source term, the flow field of the conlbustor can be calculated. Nunlerical result using the source ternl nlethod is conlpared to the experiment data acquired on direct connected scranljet test facility, The conlparison indicates that the source ternl method can predict pressure distribution of the conlbustor and can nleet the need of the vehicle configuration and integral design.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2005年第5期385-388,共4页
Journal of Propulsion Technology
