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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2015, Vol. 36 ›› Issue (7): 2166-2176.doi: 10.7527/S1000-6893.2015.0091

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Experimental study on Rayleigh-Ludwieg instability of aircraft wake vortex

BAO Feng1, LIU Jinsheng1, ZHU Rui1, LIU Yue2   

  1. 1. School of Physics and Mechanical and Electrical Engineering, Xiamen University, Xiamen 361005, China;
    2. Xiamen Institute of Technology, Huaqiao University, Xiamen 361021, China
  • Received:2015-01-27 Revised:2015-03-30 Online:2015-07-15 Published:2015-04-01
  • Supported by:

    National Natural Science Foundation of China (11072206)

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: