An Experimental Study of the Effects of Sweep Wing on the Boundary Layer of 2D Wing

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Tabrizian, Arshia | 2013

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 44600 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Soltani, Mohammad Reza; Davari, Ali Reza
Abstract:
The behavior of boundary layer under the effect of the sweep angle is considered. The measurements were performed by a pitot tube rake. Three models with various sweep angels at angles of attack -2, 0 and 2 degree were tested. Both tip and root of all wings were closed by flat plates in order to prevent the flow to roll-up. However the flow field on the wing was still three-dimensional because of the sweep angle. The velocity on the wing has two components; longitudinal and lateral. The cross flow emerges due to the non-equilibrium of pressure and centrifugal forces. The velocity profiles showed that the magnitude of cross flow was stronger near the leading edge of the wing. The cross flow velocity decreased as the angle of attack was increased. Further, the strength of the cross flow was seen to be nearly constant on the c/4 line, which is a reason for the direction of cross flow on the wing surface. Velocity power spectrum analysis showed that there was a fluctuation band around the frequency of 4 Hz. This seems to be corresponded to the stationary cross flow instability and it may cause to enhance the transition on the wing surface
Keywords:
Swept Wing ; Boundary Layer ; Experimental Investigation ; Two Dimentional Wing

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