| タイトル | Receptivity of Hypersonic Boundary Layers over Straight and Flared Cones |
| 本文（外部サイト） | http://hdl.handle.net/2060/20100002814 |
| 著者（英） | Kegerise, Michael A.; Balakumar, Ponnampalam |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2010-01-04 |
| 言語 | eng |
| 内容記述 | The effects of adverse pressure gradients on the receptivity and stability of hypersonic boundary layers were numerically investigated. Simulations were performed for boundary layer flows over a straight cone and two flared cones. The steady and the unsteady flow fields were obtained by solving the two-dimensional Navier-Stokes equations in axi-symmetric coordinates using the 5th order accurate weighted essentially non-oscillatory (WENO) scheme for space discretization and using third-order total-variation-diminishing (TVD) Runge-Kutta scheme for time integration. The mean boundary layer profiles were analyzed using local stability and non-local parabolized stability equations (PSE) methods. After the most amplified disturbances were identified, two-dimensional plane acoustic waves were introduced at the outer boundary of the computational domain and time accurate simulations were performed. The adverse pressure gradient was found to affect the boundary layer stability in two important ways. Firstly, the frequency of the most amplified second-mode disturbance was increased relative to the zero pressure gradient case. Secondly, the amplification of first- and second-mode disturbances was increased. Although an adverse pressure gradient enhances instability wave growth rates, small nose-tip bluntness was found to delay transition due to the low receptivity coefficient and the resulting weak initial amplitude of the instability waves. The computed and measured amplitude-frequency spectrums in all three cases agree very well in terms of frequency and the shape except for the amplitude. |
| NASA分類 | Aerodynamics |
| レポートNO | AIAA Paper 2010-1065
LF99-8928 |
| 権利 | No Copyright |
