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A numerical study of hypersonic laminar film cooling

Published online by Cambridge University Press:  04 July 2016

X. Yang ,
K. J. Badcock  and
B. E. Richards
X. Yang
Affiliation:
Department of Aerospace Engineering, University of Glasgow, UK
K. J. Badcock
Affiliation:
Department of Aerospace Engineering, University of Glasgow, UK
B. E. Richards
Affiliation:
Department of Aerospace Engineering, University of Glasgow, UK
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Abstract

A computational study has been performed to investigate the effectiveness of film cooling in hypersonic laminar flows. Both the primary and the coolant flow are air. First, three different primary flow conditions are used for validation. A uniform boundary condition at the slot exit is found to give unrealistic predictions of the heat transfer rate, whilst a boundary condition involving extended coolant inlet gives improvement. Then five coolant injection rates and three slot heights are examined. It is confirmed that increasing the coolant injection rate can increase the film cooling effectiveness for laminar cases. But slot height does not play an important role under the flow conditions in this study. The computational results are compared with the experimental results and good agreement is achieved.

Type
Research Article
Information
The Aeronautical Journal , Volume 107 , Issue 1074: University of Glasgow 50th year anniversary special , August 2003 , pp. 479 - 486
Copyright
Copyright © Royal Aeronautical Society 2003 

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References

1. Goldstein, R.J., Eckert, E.R.G., Tsou, F.K. and Haji-Sheikh, A., Film-cooling with air and helium injection through a rearward-facing slot into a supersonic air flow, AIAA J, 1966, 4, pp 981–985.Google Scholar
2. Kanda, T., Masuya, G., Ono, F. and Wakamatsu, Y., Effect of film cooling/regenerative cooling on scramjet engine performances, J of Propulsion and Power, 1994, 10, pp 618–624.Google Scholar
3. Stollery, J.L. and El-Ehwany, A.A.M., A note on the use of a boundary-layer model for correlating film-cooling data, Int J. Heat Mass Transfer, 1965, 8, pp 55–65.Google Scholar
4. Parthasarathy, K. and Zakkay, V., An experimental investigation of turbulent slot injection at Mach 6, AIAA J, 1970, 8, pp 1302–1307.Google Scholar
5. Spalding, D.B., Heat and mass transfer in boundary layers, part 2 film cooling, Northern Research and Engineering Corp Report No 1058-2, 1962.Google Scholar
6. O’connor, J.P. and Haji-Sheikh, A., Numerical study of film cooling in supersonic flow, AIAA J, 1992, 30, pp 2426–2433.Google Scholar
7. Richards, B.E. Film Cooling in Hypersonic Flow, 1967, PhD thesis, University of London.Google Scholar
8. Richards, B.E. and Stollery, J.L. Turbulent gaseous film cooling in hypersonic flow, 1970, The Euromech 21 meeting on Transitional and Turbulent Boundary Layers, Toulouse.Google Scholar
9. Richards, B.E. and Stollery, J.L., Laminar film cooling experiments in hypersonic flow, J Aircraft, 1979, 16, pp 177–180.Google Scholar
10. Cary, A.M. and Hefner, J.N., Film-cooling effectiveness and skin friction in hypersonic turbulent flow, AIAA J, 1972, 10, pp 1188–1193.Google Scholar
11. Zakkay, V., Wang, C.R. and Miyazawa, M., Effect of adverse pressure gradient on film cooling effectiveness, AIAA J, 1974, 12, pp 708–709.Google Scholar
12. Majeski, J.A. and Weatherford, R.H. Development of and empirical correlation for film-cooling effectiveness, 1988, AIAA Paper 88-2624.Google Scholar
13. Olsen, G.C., Nowak, R.J., Holden, M.S. and Baker, N.R. Experimental results for film cooling in 2-D supersonic flow including coolant delivery pressure, geometry, and incident shock effects, 1990, AIAA Paper 90-0605.Google Scholar
14. Takita, K., Film cooling effect of hydrogen on cylinder in supersonic airflow, J Spacecraft and Rockets, 1997, 34, pp 285–289.Google Scholar
15. Aupoix, B., Mignosi, A., Viala, S., Bouvier, F. and Gaillard, R., Experimental and numerical study of supersonic film cooling, AIAA J, 1998, 36, pp 915–923.Google Scholar
16. Takita, K. and Masuya, G., Effects of combustion and shock impingement on supersonic film cooling by hydrogen, AIAA J, 2000, 38, pp 1899–1906.Google Scholar
17. Beckwith, I.E. and Bushnell, D.M., Calculation by a finite-difference method of supersonic turbulent boundary layers with tangential slot injection, 1971, Technical report, NASA TN D-6221.Google Scholar
18. Wang, J., Prediction of turbulent mixing and film-cooling effectiveness for hypersonic flows, 1989, AIAA Paper 89-1867.Google Scholar
19. Badcock, K.J., Richards, B.E. and Woodgate, W.A., Elements of computational fluid dynamics on block structured grids using implicit solvers, Progress in Aerospace Sciences, 2000, 36, pp 351–392.Google Scholar
20. Bass, R., Hardin, L., Rodgers, R. and Ernst, R. Supersonic film cooling, 1990, AIAA Paper 90-5239.Google Scholar
21. Hansmann, T., Wilhelmi, T. and Bohn, D., An experimental investigation of the film-cooling process at high temperatures and velocities, 1993, AIAA Paper 93-5062.Google Scholar
22. Seban, R.A., Heat transfer and effectiveness for a turbulent boundary layer with tangential fluid injection, J Heat Transfer, 1960, Trans. ASME, Series C, 82, pp 303–312.Google Scholar
23. Burns, W.K. and Stosllery, J.L., The influence of foreign gas injection and slot geometry on film cooling effectiveness, Int J Heat Mass Transfer, 1969, 12, pp 935–951.Google Scholar