Loading...

Flow analysis around a pitching airfoil

Tolouei, E ; Sharif University of Technology | 2004

226 Viewed
  1. Type of Document: Article
  2. DOI: 10.2514/6.2004-5200
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2004
  4. Abstract:
  5. A series of low-speed wind tunnel tests were performed to investigate the unsteady pressure distribution over an airfoil. Dynamic pitching motion was produced by oscillating the model over a range of reduced frequencies, k=0.022 - 0.066. In addition, steady data were acquired and examined to furnish as a baseline for analysis and comparison. The model was oscillated between 0-18° angle of attack. Surface static pressure was measured from x/c=5-80% for both upper and lower surfaces. The pressure coefficients in the low angle of attack range showed little overshoot when compared with the static values, while for the large angle of attack cases the differences were significant. For a constant oscillation frequency, the hysteresis loop in the pressure data was both clockwise and counterclockwise when plotted against the angle of attack. Furthermore, the dynamic pressure signature for some pressure ports on the suction surface were higher than their corresponding static values, but for some other ports the pressure was lower than their corresponding static values. Copyright © 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved
  6. Keywords:
  7. Aerodynamics ; Wind tunnels ; Pressure distribution ; Plasma oscillations ; Hysteresis ; Frequencies ; Flow measurement ; Data acquisition ; Airfoils
  8. Source: Collection of Technical Papers - 22nd AIAA Applied Aerodynamics Conference, Providence, RI, 16 August 2004 through 19 August 2004 ; Volume 2 , 2004 , Pages 914-924 ; 10485953 (ISSN)
  9. URL: https://arc.aiaa.org/doi/10.2514/6.2004-5200