City Research Online

Abstract

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.

Publication Type:	Article
Additional Information:	© 2012 Sharif University of Technology. Production and hosting by Elsevier B.V. Open access CC-BY license.
Publisher Keywords:	Boundary layer, Spectral analysis, Instability mode, Swept wing, Transition
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics
Departments:	School of Science & Technology School of Science & Technology > Engineering
SWORD Depositor:	Symplectic Administrator

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