摘要
针对高马赫数环境下侧向反推发动机喷流的非定常干扰问题,采用数值方法求解考虑多组分掺混的N-S方程,研究锥柱组合构型喷流干扰流场的建立,获取典型时刻干扰流场分布以及气动干扰力及力矩的变化特性,分析不同高度、壁面温度以及表面气体引射条件对喷流干扰区域发展的影响。结果表明:当喷流开启后,喷管出口处燃气流与高速自由来流作用形成喷流干扰流场,在喷口上游形成分离激波,且干扰流场发展过程中分离激波逐渐前移;在有攻角条件下,背风侧分离激波前移更快,分离区域的不对称性会引起明显的气动扰动;分离激波的前移速度及最终位置对边界层厚度较敏感,当飞行高度提高、壁温增加或模型表面存在较大速度的气体引射时,边界层厚度增加,此时分离区域增大,干扰流场发展过程引起的气动扰动更加显著。
In order to study unsteady jet interaction caused by lateral retrorocket in high Mach flow,a numerical simulation method based on N-S equation with components mixed model was used to analyze the jet interaction flow field of a Cone-Cylinder configuration,the characteristics of interaction flow field distribution and aerodynamic disturbing force and moment was obtained,the influence of development of jet interference area in different height,wall temperature and gas injection conditions was also analyzed.The results show that when the jet is turned on,the gas flow at the nozzle exit interacts with the high speed free stream,which forms a jet interaction flow field,a separation shock wave is generated on the upstream position of the nozzle,and it moves towards the head of the model when the jet interaction flow develops;The separation shock wave moves faster on the leeward side when the free stream has an angle of attack,asymmetry of the flow separation area causes significant aerodynamic disturbance;The moving speed and the final balanced position of the separation shock wave is sensitive to the thickness of boundary layer,when flight altitude or wall temperature increases,or there is high velocity gas injection existed on the surface of the model,the boundary layer gets thicker,causing greater aerodynamic disturbance in the development of interaction flow field.
作者
庞川博
刘乐
李艺
PANG Chuanbo;LIU Le;LI Yi(Xi'an Mordern Control Technology Research Institute,Xi'an 710065,Shaanxi,China)
出处
《弹箭与制导学报》
北大核心
2025年第5期726-734,共9页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
侧向喷流
非定常
流动分离
喷流干扰
lateral jet
unsteady flow
flow separation
jet interaction
