Effect of Wall Temperature on Boundary Layer Transition Prediction Using Transition Model

KONG Weixuan; YAN Chao; ZHAO Rui

doi:10.7527/S1000-6893.2013.0185

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2013 , Vol. 34 >Issue 10: 2249 - 2255

DOI: https://doi.org/10.7527/S1000-6893.2013.0185

Fluid Mechanics and Flight Mechanics

Effect of Wall Temperature on Boundary Layer Transition Prediction Using Transition Model

KONG Weixuan ,
YAN Chao ,
ZHAO Rui

Expand

School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China

Received date: 2012-11-07

Revised date: 2012-12-25

Online published: 2013-02-26

Supported by

National Basic Research Program of China (2009CB72414)

Fold

Abstract

The correct prediction of boundary layer transition is essential for a successful design of hypersonic flying vehicles. In this paper, the effect of wall temperature condition on boundary layer transition prediction using a transition model is studied. Modifications are made to the time scale based on non-turbulence kinetic energy and the production term of the intermittency factor equation of k-ω-γ transition model. The effects of wall temperature condition on the maximum amplification rate and critical Reynolds number are considered when modeling the first and second mode. The influence of wall temperature on a hypersonic boundary layer of a blunt cone with small nose bluntness at zero angle of attack is investigated by the modified k-ω-γ transition model. The improved model can provide reasonable results for the maximum amplification rate and the most unstable frequency of the first oblique and two-dimensional second mode both at adiabatic and isothermal wall conditions. The transition locations predicted by the modified k-ω-γ transition model agree well with those obtained by stability analysis.

Key words： wall temperature; transition model; boundary layer; transition flow; hypersonic flow

Cite this article

KONG Weixuan , YAN Chao , ZHAO Rui . Effect of Wall Temperature on Boundary Layer Transition Prediction Using Transition Model[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013 , 34(10) : 2249 -2255 . DOI: 10.7527/S1000-6893.2013.0185

References

[1] Launius R. Hypersonic flight-evolution from X-15 to space shuttle. AIAA-2003-2716, 2003.
[2] Mack L. Linear stability theory and the problem of supersonic boundary-layer transition. AIAA Journal, 1975, 13(3): 278-289.
[3] Bountin D. Development of natural disturbances in a hypersonic boundary layer on a sharp cone. Journal of Applied Mechanics and Technical Physics, 2001, 42(1): 57-62.
[4] Malik M. Prediction and control of transition in supersonic and hypersonic boundary layers. AIAA Journal, 1989, 27(11): 1487-1493.
[5] Mayle R, Schulz A. The path to predicting bypass transition. Journal of Turbomachinery, 1997, 119: 405-411.
[6] Anderson P, Berggren M, Henningson D. Optimal disturbances and bypass transition in boundary layers. Physics of Fluids, 1999, 11: 134-150.
[7] Leib S, Wundrow D, Goldstein M. Effect of free-stream turbulence and other vortical disturbances on a laminar boundary layer. Journal of Fluid Mechanism, 1999, 380: 169-203.
[8] Warren S. Transition closure model for predicting transition onset. Journal of Aircraft, 1998, 35: 769-775.
[9] Xu D, Ma H Y. Engineering transition models for hypersonic boundary layer. Journal of the Graduate School of the Chinese Academy of Sciences, 2009, 26(1): 43-49.(in Chinese) 许丁, 马晖扬. 高超声速边界层工程转捩模式研究. 中国科学院研究生院学报, 2009, 26(1): 43-49.
[10] Song B, Li C X. Laminar-to-turbulent transition onset prediction of hypersonic flows based on laminar kinetic energy equation. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(2): 244-247.(in Chinese) 宋博, 李椿萱. 基于非湍流脉动动能方程的高超神速转捩预测. 北京航空航天大学学报, 2010, 36(2): 244-247.
[11] Wang L. Investigation of transition model for hypersonic boundary layer. Beijing: Tsinghua University, 2008.(in Chinese) 王亮. 高超音速边界层转捩的模式研究. 北京: 清华大学, 2008.
[12] Wang L. Development of an intermittency equation for the modeling of the supersonic/hypersonic boundary layer flow transition. Flow, Turbulence and Combustion, 2011, 87(1): 165-187.
[13] Zhou H. Hydrodynamic stability. Beijing: National Defense Industry Press, 2004: 177-181.(in Chinese) 周恒. 流动稳定性. 北京: 国防工业出版社, 2004: 177-181.
[14] Su C H. The transition prediction of boundary layers on a hypersonic cone and the improvement of the e^N method. Tianjin: Tianjin University, 2008.(in Chinese) 苏彩虹. 高超音速边界层的转捩预测及e^N方法的改进. 天津: 天津大学, 2008.
[15] Walker G J. Transition flow on axial turbomachine blading. AIAA Journal, 1989, 27(5): 595-602.
[16] Mack L. Boundary-layer stability theory. AGARD Report No.709, 1984.
[17] Wilcox D. Turbulence model transition prediction. AIAA Journal, 1975, 13(2): 241-243.
[18] Fisher D. In-flight transition measurement on a 10° cone at Mach number from 0.5 to 2. NASA TP-1971, 1982.

Options

Outlines

模态框（Modal）标题

Abstract

Cite this article

References