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Investigation of the pressure distribution and transition point over a swept wing

Soltani, M. R ; Sharif University of Technology | 2011

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  1. Type of Document: Article
  2. DOI: 10.1016/j.scient.2011.10.001
  3. Publisher: 2011
  4. Abstract:
  5. A series of wind tunnel tests are performed to examine the flow field over a swept wing under various conditions. The wing has a laminar flow airfoil section, similar to those of the NACA 6-series. Static pressure distributions over the upper surface of the wing, in both chordwise and spanwise directions, are measured at different angles of attack. The data is employed to predict the transition point at each chordwise section. The skewness parameter of the pressure data shows that this factor drops to zero in the transition region. A comparison of the calculated transition point on the wing surface with that obtained from the 2D computational method shows reasonable agreement over a portion of the model. The power spectral density calculated from the total pressure data of the boundary layer, over the wing surface, at several locations shows the instability modes
  6. Keywords:
  7. Spectral analysis ; Swept wing ; Angles of attack ; Instability mode ; Laminar flow airfoils ; Pressure data ; Static pressure distributions ; Total pressure ; Transition ; Transition point ; Transition regions ; Upper surface ; Wind tunnel tests ; Wing surface ; Airfoils ; Laminar flow ; Power spectral density ; Pressure distribution ; Spectral density ; Spectrum analysis ; Transition flow ; Two dimensional ; Aircraft ; Boundary layer ; Flow field ; Instability ; Numerical method ; Parameterization ; Pressure gradient ; Two-dimensional modeling ; Vehicle component ; Wind tunnel
  8. Source: Scientia Iranica ; Volume 18, Issue 6 , December , 2011 , Pages 1277-1286 ; 10263098 (ISSN)
  9. URL: http://www.sciencedirect.com/science/article/pii/S1026309811002306