摘要
超声速进气道是固体火箭冲压发动机至关重要的部件之一,直接影响燃烧室的燃烧及发动机性能。基于N-S方程、标准k-ε双方程湍流模型,利用FLUENT软件对某型固体火箭冲压发动机楔形超声速进气道内外流场进行了三维数值模拟。计算得到了超声速进气道在飞行马赫数为Ma=3.5的情况下的流场性能。并在相同马赫数下,研究了等比压缩和攻角条件下的进气道流场的分布情况。模拟结果表明:进气道的总压恢复系数和流量系数等性能指标受到攻角的影响而发生变化。
Supersonic inlet is one of the important part of solid rocket ramjet. The performance research of this inlet is one of the key techniques for solid rocket ramjet. The performance of supersonic inlet determines the pressure and the air flux in combustor, then affects the work of ramjet. In this paper, based on the N-S equation, standard k-ε turbulence model, FLUENT is used to simulate the cuniform air inlet of solid rocket ramjet. The flow field of air inlet at Mach number 3.5 is gained. Under the same Mach number, some researches on the performance of flow field of air inlet with attack angle and compression ratio with body are also performed. The simulation results indicated that total pressure recovery coefficient and mass flow coefficient of air inlet are effected by changing attack angle.
出处
《火箭推进》
CAS
2008年第3期27-30,6,共5页
Journal of Rocket Propulsion
关键词
固体火箭冲压发动机
进气道
模拟仿真
攻角
缩比
solid rocket ramjet
supersonic inlet
numerical simulation
attack angle
compression ratio
