Experimental Investigation of Asymmetric Vortex Breakdown Flow Control by Microperturbation over Highly Swept Wings
Publication: Journal of Aerospace Engineering
Volume 31, Issue 6
Abstract
An experimental investigation on asymmetric vortex breakdown flow over three delta wings with sweep angle of 85°, 80°, and 70° was carried out in a wind tunnel at high angles of attack and Reynolds number of using particle image velocimetry and pressure measurement techniques. First, vortex breakdown flow over delta wings with different sweep angles was measured to confirm the asymmetric flow phenomenon and its formation conditions. Time-averaged vortex breakdown flow over the 70° swept wing was found to be symmetric, whereas flow is asymmetric over the 80° and 85° swept wings. Instability due to crowding together of both leading-edge vortices is the cause of asymmetric vortex breakdown flow. Second, a special test that two nose sections with the same size and shape, named NT1 and NT2, was used to explore the effect of manufacturing imperfection of nose on the asymmetry of vortex breakdown flow was designed. Unpredictable manufacturing imperfection at the nose tip was found to be key natural perturbation of the instability, which led uncertain asymmetric vortex breakdown flow. Finally, the effects of an artificial spherical microperturbation with diameter of 0.2 mm fixed at the nose tip were examined to confirm the nondeterminacy of natural perturbations. With artificial microperturbations, rolling moment induced by asymmetric vortex breakdown flow can be controlled in a skillfully deflected manner.
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Acknowledgments
The project is supported by the National Natural Science Fund of China (51706228). The author thanks Prof. Deng Xueying for the help and guidance with the work in this paper.
References
Agrawal, S., R. M. Barnett, and B. A. Robinson. 1992. “Numerical investigation of vortex breakdown on a delta wing.” AIAA J. 30 (3): 584–591. https://doi.org/10.2514/3.10960.
Arena, A., and R. Nelson. 1989. “The effect of asymmetric vortex wake characteristics on a slender delta wing undergoing wing rock motion.” In Proc., 6th Atmospheric Flight Mechanics Conf., 3348. Reston, VA: AIAA.
Cai, J., Y. Cui, and H. Tsai. 2007. “A combined experimental and analytical investigation of the vortex stability over sharp-edged slender bodies.” Phys. Fluids 19 (8): 087103. https://doi.org/10.1063/1.2766739.
Chen, X. R., X. Y. Deng, Y. K. Wang, P. Q. Liu, and Z. Gu. 2002. “Influence of nose perturbations on behaviors of asymmetric vortices over slender body.” Acta Mech. Sin. 18 (6): 581–593. https://doi.org/10.1007/BF02487960.
Chen, Y., X. Y. Deng, W. Y. Kui, W. Bing, and D. Chao. 2007. “Testing technique of PIV in low-speed wind tunnel.” [In Chinese.] J. Exp. Fluid Mech. 21 (2): 78–81.
Degani, D. 1992. “Instabilities of flows over bodies at large incidence.” AIAA J. 30 (1): 94–100. https://doi.org/10.2514/3.10887.
Dong, C., X. Deng, Y. Wang, and G. Wu. 2010. “A new criterion to determine the position of vortex breakdown point.” In Vol. 1 of Proc., Asia-Pacific Int. Symp. on Aerospace Technology (APISAT2010), 137–140. Beijing, China: Chinese Society of Aeronautics and Astronautics.
Gursul, I. 2005. “Review of unsteady vortex flows over slender delta wings.” J. Aircr. 42 (2): 299–319. https://doi.org/10.2514/1.5269.
Gursul, I., and H. Yang. 1995. “On fluctuations of vortex breakdown location.” Phys. Fluids 7 (1): 229–231. https://doi.org/10.1063/1.868724.
Keener, E. R., and G. T. Chapman. 1977. “Similarity in vortex asymmetries over slender bodies and wings.” AIAA J. 15 (9): 1370–1372. https://doi.org/10.2514/3.60795.
Kohlman, D. L., and J. W. H. Wentz. 1971. “Vortex breakdown on slender sharp-edged wings.” J. Aircr. 8 (3): 156–161. https://doi.org/10.2514/3.44247.
Lamont, P., and B. Hunt. 1976. “Pressure and force distributions on a sharp-nosed circular cylinder at large angles of inclination to a uniform subsonic stream.” J. Fluid Mech. 76 (3): 519–559.https://doi.org/10.1017/S0022112076000773.
Lowson, M., and A. Ponton. 1992. “Symmetry breaking in vortex flows on conical bodies.” AIAA J. 30 (6): 1576–1583. https://doi.org/10.2514/3.11103.
Lowson, M., and A. Riley. 1995. “Vortex breakdown control by delta wing geometry.” J. Aircr. 32 (4): 832–838. https://doi.org/10.2514/3.46798.
Menke, M., and I. Gursul. 1997. “Self-excited oscillations of vortex breakdown location over delta wings.” In Proc., 35th Aerospace Sciences Meeting and Exhibit, 744. Reston, VA: AIAA.
Menke, M., H. Yang, and I. Gursul. 1999. “Experiments on the unsteady nature of vortex breakdown over delta wings.” Exp. Fluids 27 (3): 262–272. https://doi.org/10.1007/s003480050351.
Payne, F., T. Ng, R. Nelson, and L. Schiff. 1988. “Visualization and wake surveys of vortical flow over a delta wing.” AIAA J. 26 (2): 137–143. https://doi.org/10.2514/3.9864.
Polhamus, E. C. 1971. “Predictions of vortex-lift characteristics by a leading-edge suction analogy.” J. Aircr. 8 (4): 193–199. https://doi.org/10.2514/3.44254.
Rusak, Z., and D. Lamb. 1999. “Prediction of vortex breakdown in leading-edge vortices above slender delta wings.” J. Aircr. 36 (4): 659–667. https://doi.org/10.2514/2.2508.
Stahl, W., M. Mahmood, and A. Asghar. 1992. “Experimental investigations of the vortex flow on delta wings at high incidence.” AIAA J. 30 (4): 1027–1032. https://doi.org/10.2514/3.11023.
Xiao, Z., H. Chen, S. Fu, and F. Li. 2004. “Asymmetrical vortices breakdown of delta wing at high incidence. In Proc., 22nd Applied Aerodynamics Conf. Exhibit, 4728. Reston, VA: AIAA.
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Published In
Journal of Aerospace Engineering
Volume 31 • Issue 6 • November 2018
Copyright
©2018 American Society of Civil Engineers.
History
Received: Dec 19, 2017
Accepted: Apr 27, 2018
Published online: Aug 13, 2018
Published in print: Nov 1, 2018
Discussion open until: Jan 13, 2019
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