【作者】 韩光；

【导师】 陈少松；

【作者基本信息】 南京理工大学 ， 流体力学， 2006， 硕士

【摘要】 本文对冲压增程弹丸所用发动机的双锥超声速进气道在各种工况条件下的流场进行了数值模拟，给出了进气道流场的等压线图、等密度线图和等马赫线图，从而观察在不同的锥尖角组合、锥芯与外罩唇口的相对位置、出口反压、来流马赫数和攻角时，对进气道流场及性能参数的影响，并探讨喘振现象的产生机理及诱导因素，以便确定最佳的工作状态，得到最优的进气道模型。通过建立三维结构化网格模型，选择合适的数值格式与湍流模型，对进气道流场进行数值模拟，得到了合理的结果。同时对以上某型号的进气道模型进行了风洞实验，并与数值模拟的结果进行了对比，其误差率在允许的范围之内，这也进一步验证了所用数值模拟方法的可靠性。因此，上述有关方法和结论将为增程弹丸进气道的设计与更深入地研究提供重要的理论依据。更多还原

【Abstract】 This paper referred to simulating the supersonic double cone inlet’ s flow field of ramjet pill assisted range projectiles at a variety of working circumstances, pressure contours, density contours and Mach number contours of inlet’ s flow field were given’ When cone combination, relative location of cone core and cowl lip, the pressure of outlet, inflow Mach number and angle were changed, flow field and performance parameters of inlet can be affected. Simultaneity, productive mechanism and inducing factors of the inlet surge were also discussed. Then the best working conditions and the best model of inlet were obtained. After inlet model’ s three dimensional structural grid was generated, proper numerical scheme and onflow model were choosed, then numerical computation on flow field of inlet was taken, finally the better results were got. At the same, wind-tunnel experimental research about some inlet model was fulfilled. Then, results of wind-tunnel experiment and results of numerical simulation were comparised, error ratio was under permission range, which ulteriorly validated the reliability of numerical simulation method. Therefore, the conclusions and method of this paper can be helpful to design the inlet of improved range’s cannonball theoretically and technologically.更多还原