Paper Title:
Experimental Investigation on Improving the Aerodynamic Performance of Swept Aircraft by DBD Plasma
  Abstract

The experimental investigation on improving the aircraft aerodynamic performance by DBD (Dielectric Barrier Discharges) plasma is described in this paper. The test has been carried out in a low speed wind tunnel with a wept aircraft model. The plasma actuators were set on the upper surface of swept wing combining with airplane body model. The test results presented include the flow field visualization by PIV (Particle Imaging Velocimetry), lift and drag characteristics under the plasma actuators off and on. The results show that the induced flow by DBD plasma may control the separation on the upper surface of the wing evidently, so that the highest stalling angle of the model increases and maximum lift-to-drag ratio rises, respectively. But with the wind velocity increasing, the effect of the plasma decreases gradually.

  Info
Periodical
Chapter
Chapter 15: Meso/Micro Manufacturing Equipment and Processes
Edited by
Wu Fan
Pages
3234-3242
DOI
10.4028/www.scientific.net/AMM.110-116.3234
Citation
W. He, Z. G. Niu, B. Pan, Q. Lin, "Experimental Investigation on Improving the Aerodynamic Performance of Swept Aircraft by DBD Plasma", Applied Mechanics and Materials, Vols. 110-116, pp. 3234-3242, 2012
Online since
October 2011
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Price
$32.00
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