Applications of Fluid MechanicsNo Access

Dynamic stall control using inflatable leading edge

National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an 710072, P. R. China

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He-Yong Xu

National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an 710072, P. R. China

E-mail Address: xuheyong@nwpu.edu.cn

Corresponding author.

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Zheng-Yin Ye

National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an 710072, P. R. China

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Ming-Sheng Ma

National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an 710072, P. R. China

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, and

Yue Xu

Chinese Aeronautical Establishment, Beijing 100029, P. R. China

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https://doi.org/10.1142/S0217979220401086Cited by:4 (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

The inflatable leading edge (ILE) as a dynamic stall control concept for helicopter rotor blades was investigated numerically on a dynamically pitching airfoil. A fluid–structure interaction (FSI) numerical method for the elastic membrane structure was constructed based on unsteady Reynolds-averaged Navier–Stokes (URANS) equations and mass spring damper (MSD) structural dynamic model. The numerical results indicate that the ILE can change the radius of curvature of the airfoil leading edge, which could reduce the streamwise adverse pressure gradient and suppress the formation of dynamic stall vortex (DSV). Although the maximum lift coefficient of the airfoil is reduced by 8.2%, the maximum drag and pitching moment coefficients of the airfoil are reduced by up to 50.1% and 55.3%, respectively.

Keywords:

PACS: 47.62.+q

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References

1. W. J. McCroskey, The phenomenon of dynamic stall, Tech. Rep., Tech. Rep. NASA-TM-81264 (1981). Google Scholar
2. J. A. Ekaterinaris, M. S. Chandrasekhara and M. F. Platzer, AIAA Paper 2005-1296 (2005). Google Scholar
3. F. Richez, J. Am. Helicopter Soc. 63, 022006 (2018). Crossref, Web of Science, Google Scholar
4. D. Feszty, E. A. Gillies and M. Vezza, AIAA J. 42, 17 (2004). Crossref, ADS, Google Scholar
5. G. Q. Zhao and Q. J. Zhao, Chinese J. Aeronaut. 27, 1051 (2014). Crossref, Web of Science, Google Scholar
6. C. G. Matalanis et al., AIAA J. 55, 3001 (2017). Crossref, ADS, Google Scholar
7. W. Geissler and G. Dietz, Dynamic stall control investigation on a full size chord blade section, in 30th European Rotorcraft Forum, Marseille, France, 14–16 September 2004. Google Scholar
8. R. J. Benney and K. R. Stein, J. Aircr. 33, 730 (1996). Crossref, Web of Science, Google Scholar
9. W. Zhang, Y. Jiang and Z. Ye, Eng. Appl. Comput. Fluid Mech. 1, 253 (2007). Google Scholar
10. C. B. Lee, Phys. Lett. A 247, 397 (1998). Crossref, Web of Science, ADS, 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. Y. D. Zhu et al., Phys. Fluids 30, 011701 (2018). Crossref, Web of Science, Google Scholar
13. W. J. McCroskey, NASA-TM-84245 (1982). Google Scholar