钝体头部边界层“逾越”型转捩机理研究

基金项目: 国家自然科学基金(1032100210672012)

Study of bypass transition mechanisms in the boundary layer of blunt bodies

1.
China Aerodynamics Research and Development Center, Mianyang 621000, China
2.
National Computational Fluid Dynamics Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
3.
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
4.
China Academe of Aerospace Aerodynamics, Beijing 100074, China

摘要: 利用数值模拟的方法,研究了再入条件下,钝头体边界层中一种新的失稳机制.这种失稳机制无法用线性稳定性理论解释.最近的研究工作表明,流动中存在着一种与局部有限幅值扰动相关的失稳机制.它与常规的T-S波或二次失稳的过程不同.数值模拟了受空间模式的局部扰动影响的钝体头部超声速边界层的失稳过程.在模拟中,明确了不同扰动模型非线性相互作用的物理机制.
- 航空、航天推进系统 /
- 紧致格式 /
- 非线性 /
- 边界层 /
- 转捩 /
- 钝体
Abstract: A new instability mechanism in the boundary layer of blunt bodies was studied under reentry conditions by using numerical simulation method.The instability mechanism cannot be addressed by linear instability theory.The recent research shows that,there is a nonlinear instability mechanism associated with local finite amplitude disturbance,which differs from the ordinary instability with respect to the T-Swave and secondly instability.The instability process under the influence of the local disturbance in the boundary layer of blunt bodies was simulated numerically.The physical mechanisms for nonlinear interaction of various disturbance modes were identified in the simulation.
- aerospace propulsion system /
- compact scheme /
- boundary layer /
- nonlinear /
- transition /
- blunt body

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