...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of Fluid Mechanics >Leading-edge receptivity to free-stream disturbance waves for hypersonic flow over a parabola
【24h】

Leading-edge receptivity to free-stream disturbance waves for hypersonic flow over a parabola

机译：抛物线上高超声速流对自由流扰动波的前沿接受性

获取原文
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

The receptivity of hypersonic boundary layers to free-stream disturbances, which is the process of environmental disturbances initially entering the boundary layers and generating disturbance waves, is altered considerably by the presence of bow shocks in hypersonic flow fields. This paper presents a numerical simulation study of the generation of boundary layer disturbance waves due to free-stream waves, for a two-dimensional Mach 15 viscous flow over a parabola. Both steady and unsteady flow solutions of the receptivity problem are obtained by computing the full Navier-Stokes equations using a high-order-accurate shock-fitting finite difference scheme. The effects of bow-shock/free-stream-sound interactions on the receptivity process are accurately taken into account by treating the shock as a discontinuity surface, governed by the Rankine-Hugoniot relations. The results show that the disturbance waves generated and developed in the hypersonic boundary layer contain both first-, second-, and third-mode waves. A parametric study is carried out on the receptivity characteristics for different free-stream waves, frequencies, nose bluntness characterized by Strouhal numbers, Reynolds numbers, Mach numbers, and wall cooling. In this paper, the hypersonic boundary-layer receptivity is characterized by a receptivity parameter defined as the ratio of the maximum induced wave amplitude in the first-mode-dominated region to the amplitude of the free-stream forcing wave. It is found that the receptivity parameter decreases when the forcing frequency or nose bluntness increase. The results also show that the generation of boundary layer waves is mainly due to the interaction of the boundary layer with the acoustic wave field behind the bow shock, rather than interactions with the entropy and vorticity wave fields. [References: 26]
机译：高超声速边界层对自由流扰动的接受度，这是环境扰动最初进入边界层并产生扰动波的过程，由于高超声速流场中弓形激波的存在而大大改变。本文针对抛物线上的二维马赫数15粘性流，提出了由于自由流波而产生边界层扰动波的数值模拟研究。接受性问题的稳态和非稳态流动解都可以通过使用高阶精度的冲击拟合有限差分方案计算完整的Navier-Stokes方程来获得。通过将冲击视为由兰金-休格尼奥特关系控制的不连续表面，可以准确地考虑弓形冲击/自由流-声相互作用对接受过程的影响。结果表明，在高超声速边界层中产生和发展的扰动波包含第一，第二和第三模式波。对不同自由流波，频率，以Strouhal数，雷诺数，马赫数和壁冷却为特征的鼻子钝性的接受特性进行了参数研究。在本文中，高超声速边界层接受度的特征在于接受度参数，该参数定义为第一模式控制区域中最大感应波振幅与自由流强迫波振幅之比。发现当强迫频率或鼻子钝度增加时，接受度参数降低。结果还表明，边界层波的产生主要是由于边界层与弓激波后的声波场的相互作用，而不是与熵波和涡旋波场的相互作用。 [参考：26]

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号