Experimental Fluid DynamicsNo Access

The effect of concave roughness on the hypersonic flat-plate boundary-layer transition

Shuo Chen

State Key Laboratory of Turbulence and Complex Systems, Collge of Engineering, Peking University, Beijing 100871, P. R. China

E-mail Address: cspku@pku.edu.cn

Search for more papers by this author

https://doi.org/10.1142/S0217979220400913Cited by:1 (Source: Crossref)

This article is part of the issue:

Special Issue — Proceedings of the Eighth International Symposium on Physics of Fluids (ISPF8), 10–13 June, 2019, Xi'an, China

Abstract

In order to reveal the effect of aircraft surface concave roughness on the transition, several hypersonic quiet wind tunnel tests were carried out on the flat-plate model with independent concave roughness on the surface. The experimental Mach number was 6.5 and the total temperature was 430 K. Using infrared thermal imaging technology, a general rule of the effect of concave roughness on the boundary layer transition was obtained. The flow visualization results and the PCB pressure measurement results showed that the concave roughness promotes the transition by increasing the growth of the first mode wave rather than the growth of the second mode wave.

Keywords:

PACS: 47.20.lb, 47.40.ki

You currently do not have access to the full text article.
Recommend the journal to your library today!

References

1. C. B. Lee and J. Wu, Appl. Mech. Rev. 61, 03082 (2008). Crossref, Web of Science, Google Scholar
2. C. B. Lee and R. Li, J. Turbul. 8, N55 (2007). Crossref, Web of Science, ADS, Google Scholar
3. C. B. Lee and S. Fu, Exp. Fluids 30, 354 (2001). Crossref, Web of Science, ADS, Google Scholar
4. C. B. Lee et al., Exp. Fluids 28, 243 (2000). Crossref, Web of Science, Google Scholar
5. C. B. Lee, Rev. E 62, 3659 (2000). Google Scholar
6. C. B. Lee and X. Y. Jiang, Phys. Fluids 31, 111301 (2019). Crossref, Web of Science, ADS, Google Scholar
7. L. M. Mack. Boundary-layer stability theory, Doc. 900-277, Jet Propulsion Laboratory, Pasadena, California (United States) (1969). Google Scholar
8. J. M. Kendall, AIAA J. 13, 290 (1975). Crossref, ADS, Google Scholar
9. J. M. Kendall, A. Demetriades and J. C. Donaldson, AIAA J. 34, 2484 (1996). Crossref, ADS, Google Scholar
10. K. Stetson et al., Nosetip bluntness effects on cone frustum boundary layer transition in hypersonic flow, 16th Fluid and Plasmadynamics Conf., AIAA Paper 1983-1763 (1983). Crossref, Google Scholar
11. X. Chen, Y. D. Zhu and C. B. Lee, J. Fluid Mech. 820, 693 (2017). Crossref, Web of Science, ADS, Google Scholar
12. X. Chen, G. L. Huang and C. B. Lee, J. Fluid Mech. 865, 1 (2019). Crossref, Web of Science, ADS, Google Scholar
13. Y. D. Zhu et al., Phys. Fluids 30, 011701 (2018). Crossref, Web of Science, Google Scholar
14. Y. D. Zhu et al., J. Fluid Mech. 855, 152 (2018). Crossref, Web of Science, ADS, Google Scholar
15. W. F. Si et al., Phys. Fluids 31, 051702 (2019). Crossref, Web of Science, Google Scholar
16. C. B. Lee and S. Y. Chen, Natl. Sci. Rev. 6, 155 (2019). Crossref, Web of Science, Google Scholar
17. C. H. Zhang and C. B. Lee, J. Vis. 20, 7 (2017). Crossref, Web of Science, Google Scholar
18. C. H. Zhang, Phys. Lett. A 247, 397 (1998). Crossref, Web of Science, Google Scholar
19. C. H. Zhang, Q. Tang and C. B. Lee, Acta Mech. Sin. 29, 48 (2013). Crossref, Web of Science, ADS, Google Scholar
20. C. H. Zhang et al., AIP Adv. 5, 107 (2015). Google Scholar
21. Q. Tang et al., Phys. Fluids 27, 064105 (2015). Crossref, Web of Science, Google Scholar