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Two dimensional direct numerical simulation of nonreacting confined supersonic mixing layer

Published online by Cambridge University Press:  04 July 2016

D. Chakraborty ,
H. S. Mukunda  and
P. J. Paul
D. Chakraborty
Affiliation:
Aerodynamics Division, Vikram Sarabhai Space Centre, Thiruvananthapuram, India
H. S. Mukunda
Affiliation:
Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India
P. J. Paul
Affiliation:
Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India
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Abstract

Direct Numerical Simulation (DNS) results are presented for high speed nonreacting mixing layer in a confined test section. The hyper-velocity mixing layer experiment of Erdos et al with H2/N2 stream is simulated by discretizing two dimensional Navier Stokes equation using a higher order (fourth order spatial and second order temporal) compact numerical algorithm. A favourable comparison of the computation with experimentally measured wall static pressure forms the basis of further analysis. Instantaneous flow picture and the mean profiles of various flow variables were examined to determine the development and general characteristics of the confined mixing layer. It has been found that the growth of the mixing layer is towards the high speed side of the layer. Various turbulence quantities were derived from the stored time series data of the DNS calculation and the results were compared with the experimental results of supersonic free shear layer as no experimental results of turbulence statistics are available for the confined hypervelocity mixing layer. The increasing Reynolds stress data with the flow direction indicate that the turbulence is sustained by transferring the energy from the mean flow to the fluctuating field as the shear layer develops. Although the Reynolds stress is negligible in the most portion of the wall boundary layers, effect of counter gradient effect is observed in the far downstream location of the lower wall boundary layer. The general conclusion that for the supersonic mixing layer, various turbulence quantities like Reynolds stress, turbulence intensities (both streamwise and transverse) decrease with the increase in the convective Mach number is also confirmed by our results.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1036 , June 2000 , pp. 291 - 296
Copyright
Copyright © Royal Aeronautical Society 2000 

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References

1. Papamschou, D. and Roshko, A. The compressible turbulent shear layer :an experimental study, J Fluid Mechanics, 1988. 197, pp 453–457.Google Scholar
2. Saminy, M. and Elliot, G.S Effect of compressibility on the character istics of free shear layers, AIAA J 1990. 28, pp 439–445.Google Scholar
3. Goebel, S.G. and Dutton, J.C. Experimental study of compressible turbulent mixing layers, AIAA J 1991. 29, pp 538–546 Google Scholar
4. Hall, J.L. Experimental investigation of structure, mixing and combus tion in compressible turbulent shear layers, PhD Thesis, California Institute of Technology 1991.Google Scholar
5. Clemens, N.T. and Mungal, M.G. Two and three dimensional effects in the supersonic mixing layers, AIAA J 1992. 30, pp 973–981.Google Scholar
6. Elliott, G.S., Saminy, M. and Arnett, S.A. The characteristics and evo lution of large scale structures in compressible mixing layers, Physics of Fluids, 1995, 7, pp 864–876.Google Scholar
7. Racab, S.A. and Wu, J.L. Linear instabilities in two dimensional com pressible mixing layer, Physics of Fluids, 1989, A1, pp 957–966.Google Scholar
8. Jackson, T.L. and Grosch, C.E. Absolute/convective instabilities and the convective mach number in a compressible mixing layer, Physics of Fluids, 1990. A2, pp 949–954.Google Scholar
9. Lele, S.K. Direct numerical simulation of compressible free shear layer, 1989. AIAA Paper No. 89-0374.Google Scholar
10. Liou, T., Lien, W. and Huang, P. Compressibility effects and mixing enhancements in turbulent free shear layers, AIAA J 1995. 33, pp 2332–2338.Google Scholar
11. Lele, S.K. Compressibility effect on turbulence. Annual Review of Fluid Mechanics, 1994. 26, pp 211–254.Google Scholar
12. Shyy, W. and Krishnamurthy, V.S. Compressibility effects in model ing complex turbulent flows. Progress in aerospace sciences, 1997. 33, pp 587–645.Google Scholar
13. Erdos, J., Tamagno, J., Bakos, R. and Trucco, R. Experiments on shear layer mixing at hypervelocily conditions, 1992. AIAA-92-0628.Google Scholar
14. Grubber, M.R., Messersmith, N.L. and Dutton, J.C. Three dimensional velocity field in a compressible mixing layer, 1993. AIAA 31, pp 2061–2067.Google Scholar
15. Barre, S., Quine, C. and Dussauge, J.P. Compressibility effect on the structure of supersonic mixing layers, J Fluid Mechanics, 1994. 259, pp 47–78.Google Scholar
16. Guirguis, R.H., Grinstein, F.F., Young, T.R., Oran, E.S., Kailashnath, K. and J.P. BORRIS Mixing enhancement in supersonic shear layers, 1987.AIAA Paper 87-0373.Google Scholar
17. Faruk, B., Oran, E.S. and Kailashnath, K. Numerical simulation of the structure of supersonic shear layers. Physics of Fluids. 1991. A3, pp 2786–2798.Google Scholar
18. Lu, P.J. and Wu, K.C. Numerical investigation on the structure of a confined supersonic mixing layer, Physics of Fluids, 1991 A3, pp 3063–3069.Google Scholar
19. Tam, C.K.W. and Hu, F.Q. The instability and acoustic wave modes of supersonic mixing layer inside a rectangular channel, J Fluid Mechan ics, 1989. 203, pp 5l–76.Google Scholar
20. Greengough, J.A., Riley, J.J., Soetrisno, M.and Eberhardt, D.S. The effect of walls on a compressible mixing layer, 1989. AIAAPaper 89- 0372.Google Scholar
21. Zhuang, M., Dimotakis, P.E. and Kubota, Toshi The effect of walls on a spatially growing supersonic shear layer, Physics of Fluids, 1990. A2, pp 599–604.Google Scholar
22. Morris, P.J., Giridharan, M.G. and Viswanathan, K. Turbulent mixing in plane and ax (symmetric shear layer, 1990, AIAAPaper 90-0708.Google Scholar
23. Giridharan, M.G. and Morris, P.J. The development of wave packets in supersonic shear layer, 1991, AIAAPaper 91-0626.Google Scholar
24. Drummond, J. P. Supersonic reacting internal flow field, in Numerical Approaches in Combustion Modeling edited by Oran, E.S. and Borris, J.P., Progress in Aeronautics and Astronautics, 1991. 135, pp 365–420.Google Scholar
25. Carpenter, M.H. and Kamath, H. Three dimensional extension to the SPARK combustion code NASA-Langley, 1988. NASA-CP-5029, pp 107–137.Google Scholar
26. Carpenter, M.H. A generalized chemistry version of SPARK 1998. NASA-CR-4196Google Scholar
27. Koochesfahani, M.M., Dimotakis, P.E., and Broadwell, J.E. A ‘Flip' experiment in a chemically reacting turbulent mixing layer, AIAA 1985. 23,-pp 1191.Google Scholar