飞机尾涡系Rayleigh-Ludwieg不稳定性实验研究

doi:10.7527/S1000-6893.2015.0091

Abstract

Abstract:

Based on the fact that the main wing and tail would produce counter-rotating vortices in the process of taking-off and landing, a set of double vortex generators are designed. Under two different experimental conditions, in terms of changing the position and initial intensity ratio of the double vortex, the wake vortex development of the test mode is acquired, including flow visualizations and particle image velocimetry (PIV) technology. Research reveals that the introduction of a weaker vortex, with a proper position and initial intensity ratio, would change the main vortex original trajectory and promotes its dissipation. However, it does not present an obvious linear relationship between them. The analysis results of vortex trajectory could be used in improving the efficiency of taking-off and landing in airports, the experiments also provide a reference for the overall design of aircrafts: when the requirement for flight mechanics design is satisfied, optimizing the overall aerodynamic layout will have a significant effect on alleviating the intensity of aircraft wake.

Key words: aircraft wake vortex, Rayleigh-Ludwieg instability, flow visualization, particle image velocimetry (PIV), low Reynolds number flow

CLC Number:

V211.76

BAO Feng, LIU Jinsheng, ZHU Rui, LIU Yue. Experimental study on Rayleigh-Ludwieg instability of aircraft wake vortex[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(7): 2166-2176.

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Experimental study on Rayleigh-Ludwieg instability of aircraft wake vortex

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