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Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets

Published online by Cambridge University Press:  03 February 2016

Y. Fan ,
J. Chang ,
W. Bao  and
D. Yu
Y. Fan
Affiliation:
[email protected]
J. Chang
Affiliation:
[email protected]
W. Bao
Affiliation:
[email protected]
D. Yu
Affiliation:
Harbin Institute of Technology, China
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Abstract

The unsteady flowfield of a series of mixed-compression hypersonic inlets with different bleeding rates were numerically simulated. Firstly unstart oscillatory flow of hypersonic inlets caused by downstream massflow choking was discussed. Then the effects of boundary layer bleeding on the averaged performance parameter of hypersonic inlets, and on the dominant amplitude and frequency of unstart oscillatory flow of hypersonic inlets were presented. The reasons why the boundary-layer bleeding can suppress unstart oscillatory flow of hypersonic inlets were analysed. In conclusion, the averaged performance parameter of hypersonic inlets during a big buzz is improved greatly, and the dominant frequency of unstart oscillatory flow of hypersonic inlets is reduced in contrast with no bleeding, and all these are benefit to the design and operation of hypersonic inlets.

Type
Research Article
Information
The Aeronautical Journal , Volume 114 , Issue 1157 , July 2010 , pp. 445 - 450
Copyright
Copyright © Royal Aeronautical Society 2010 

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References

1. Campbell, D.H., F-12 series aircraft propulsion system performance and development, J Aircr, 1974, 11, (11), pp 670–676.Google Scholar
2. Seddon, J. and Goldsmith, E.L., Intake Aerodynamics, AIAA Educational Series, AIAA, Washington DC, USA, 1989, pp 149–168.Google Scholar
3. Tan, H., Sun, S. and Yin, Z., Oscillatory flows of rectangular hypersonic inlet unstart caused by downstream mass-flow choking, J Propul and Power, 2009, 25, (1), pp 138–147.Google Scholar
4. Wang, C., Tian, X., Cheng, K. and Wu, Y., Numerical analysis of pseudo-shock flow diffusion phenomenon in variable cross-section ducts, Proc IMechE, Part G: J Aerospace Engineering, 2008, 222, (8), pp 1109–1121.Google Scholar
5. Mahapatra, D. and Jagadeesh, G., Shock tunnel studies on cowl/ramp shock interactions in a generic scramjet inlet, Proc IMechE, PartG: J Aerospace Engineering, 2008, 222, (8), pp 1183–1191.Google Scholar
6. Liang, J., Fan, X., Wang, Y. and Liu, W., Performance enhancement of three-dimensional hypersonic inlet with sidewall compression, Proc IMechE, Part G: J Aerospace Engineering, 2008, 222, (8), pp 1211–1219.Google Scholar
7. Haberle, J. and Gulhan, A., Experimental investigation of a two-dimensional and a three-dimensional scramjet inlet at Mach 7, AIAA J Propulsion and Power, 2008, 24, (5), pp 1023–1034.Google Scholar
8. Haberle, J. and Gulhan, A., Investigation of two-dimensional scramjet inlet flowfield at Mach 7, AIAA J Propulsion and Power, 2008, 24, (3), pp 446–459.Google Scholar
9. Chang, J., Bao, W., Yu, D., Fan, Y., Shen, Y. and Zhou, W., Hypersonic inlet control with pulse periodic energy addition, Proc IMechE, Part G: J Aerospace Engineering, 2009, 223, (2), pp 85–94.Google Scholar
10. Chang, J., Bao, W., Fan, Y. and Yu, D., Performance optimization of hypersonic inlets with pulse periodic energy addition, Proc IMechE, Part G: J Aerospace Engineering, 2009, 223, (6), pp 691–699.Google Scholar
11. Yu, D., Chang, J., Bao, W. and Xie, Z., Optimal classifications crite-rions of hypersonic inlet start/unstart, J Propulsion and Power, 2007, 23, (2), pp 310–316.Google Scholar
12. Chang, J., Yu, D., Bao, W., Xie, Z. and Fan, Y., A CFD assessment of classifications for hypersonic inlet start/unstart phenomena, Aeronaut J, April 2009, 113, (1142), pp 263–271.Google Scholar
13. Chang, J., Yu, D., Bao, W. and Fan, Y., Operation pattern classification of hypersonic inlets, Acta Astronautica, 2009, 65, (3-4), pp 457–466.Google Scholar
14. Sang, D.K., Aerodynamic design of a supersonic inlet with a parametric bump, AIAA J Aircr, 2009, 46, (1), pp 198–202.Google Scholar
15. Owens, L., Allan, B. and Gorton, S., Boundary-layer-ingesting inlet flow control, AIAA J Aircr, 2009, 45, (4), pp 1431–1440.Google Scholar
16. Chang, J., Yu, D., Bao, W. and Qu, L., Dimensionless analysis of the unstart boundary for 2-D mixed hypersonic inlets, Aeronaut J, September 2008, 112, (1135), pp 547–555.Google Scholar
17. Chang, J., Fan, Y., Bao, W. and Yu, D., Unstart margin control of hypersonic inlets, Acta Astronautica, 2010, 66, (1-2), pp 78–87.Google Scholar
18. Cui, T., Yu, D., Chang, J. and Bao, W., Topological geometry interpretation of supersonic inlet start/unstart-catastrophe, hysteresis and bifurcation, AIAA J Aircr, 2008, 45, (4), pp 1464–1468.Google Scholar
19. Cui, T., Yu, D., Chang, J. and Bao, W., Catastrophe model for supersonic inlet start/unstart, AIAA J Aircr, 2009, 46, (4), pp 1160–1166.Google Scholar
20. Wagner, J.L., Yuceil, K.B., Valdivia, A., Clemens, N.T. and Dolling, D.S., Experimental investigation of unstart in an inlet/isolator model in Mach 5 flow, AIAA J, 2009, 47, (6), pp 1528–1542.Google Scholar
21. Tan, H. And Guo, R., Experimental study of the unstable–unstarted condition of a hypersonic inlet at Mach 6, J Propulsion and Power, 2007, 23, (4), pp 783–788.Google Scholar
22. Morris, M.J., Experimental investigation of normal shock/turbulent boundary layer interactions with and without mass removal, AIAA J, 1992, 30, (2), pp 359–366.Google Scholar
23. Délery, J.M., Shock wave/turbulent boundary layer interaction and its control, Progress in Aerospace Sciences, 1985, 22, pp 209–280.Google Scholar
24. Smith, A.N., Control of normal shock wave/turbulent boundary-layer interaction using streamwise grooves, AIAA Paper 2002-0978, 2002.Google Scholar
25. Hafenrichter, E.S. and Lee, Y., Experiments on normal shock/boundary layer interaction control using aeroelastic mesoflaps, AIAA Paper 2001-0156, 2001.Google Scholar
26. Mitani, T., Sakuranaka, N., Tomioka, S. and Kobayashi, K., Boundary layer control in Mach 4 and Mach 6 scramjet engines, J Propulsion and Power, 2005, 21, (4), pp 636–641.Google Scholar
27. Kouchi, T., Mitani, T. and Masuya, G., Numerical simulations in scramjet combustion with boundary layer bleeding, J Propulsion and Power, 2005, 21, (4), pp 642–649.Google Scholar
28. Trapier, S., Duveau, P. and Deck, S., Experimental study of supersonic inlet buzz, AIAA J, 2007, 44, (10), pp 2354–2365.Google Scholar
29. Chang, J. and Fan, Y., Effects of boundary layers bleeding on performance parameters of hypersonic inlets, Aircraft Engineering and Aerospace Technology, 2009, 81, (3), pp 204–211.Google Scholar
30. Chang, J., Yu, D., Bao, W., Fan, Y. and Shen, Y., Effects of boundary layers bleeding on unstart/restart characteristics of hypersonic inlets, Aeronaut J, May 2009, 113, (1143), pp 319–327.Google Scholar
31. Chang, J., Bao, W., Yu, D. and Fan, Y., Effects of wall cooling on performance parameters of hypersonic inlets, Acta Astronautica, 2009, 65, (3-4), pp 467–476.Google Scholar