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

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 direc...

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Bibliographic Details
Published inScientia Iranica Vol. 18; no. 6; pp. 1277 - 1286
Main Authors Soltani, M.R., Ghorbanian, K., Masdari, M.
Format Journal Article
LanguageEnglish
Published Elsevier B.V 01.12.2011
Subjects
Boundary layer
Instability mode
Spectral analysis
Swept wing
Transition
Transition
Swept wing
Instability mode
Spectral analysis
Boundary layer
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Summary: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.
ISSN:1026-3098
DOI:10.1016/j.scient.2011.10.001