| 摘要: |
| 根据有旋特征线理论,设计出了沿程马赫数下降规律可控的轴对称基准流场,分析了基准流场的几何参数(前缘压缩角及中心体半径)的影响规律,发现选取较小的前缘压缩角和中心体半径有利于得到性能优良的基准流场；然后在设计状态Ma=6时研究了三种典型的马赫数下降规律对这种轴对称流场性能的影响。最后考虑了粘性的影响,并进行了粘性修正探索,结果表明,采用附面层位移厚度修正方法后,基准流场的壁面压力分布和无粘情况吻合良好。 |
| 关键词: 高超内收缩进气道 基准流场 数值模拟 等马赫数梯度 |
| DOI： |
| 分类号: |
| 基金项目: |
|
| Investigation on Basic Flowfield with Controlled Mach Number Gradient for Hypersonic Inward Turning Inlets |
|
ZHU Wei, ZHANG Kun-yuan, NAN Xiang-jun
|
|
(College of Energy and Power,Nanjing University of Aeronautics and Astronautics, Nanjing 210016,China)
|
| Abstract: |
| Basic flowfields are vital for streamline traced hypersonic inward turning inlets.With the method of characteristics (MOC) and wall Mach number distribution to study basic flowfield of hypersonic inlet,the effects of basic flowfield geometry parameter and three typical wall Mach number distribution on basic flowfield were studied at Ma=6. The results indicate that the basic flowfield with small leading edge deflection angle and center body radius could have better performances. Finally,visous correction was studied considering the influence of viscous, using the method of boundary layer displacement thickness, the viscous performance parameters of design state are closer to the inviscid design parameters. |
| Key words: Hypersonic inward turning inlets Basic flowfield Numerical simulation Constant Mach number gradient |
