Experimental Study of the Pressure Distribution on the Surface of an Infinite Wing  Influenced by Different Sweep Angles

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Tirandaz, Mohammad Rasoul | 2013

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 44171 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Soltani, Mohammad Reza
Abstract:
A series of wind tunnel tests were performed to examine the effects of wing sweep and wing tip vortices on the pressure distribution of the upper surface of three wings with sweep angles of 23,33 and 40 degrees. The wing section had a laminar flow airfoil similar to that of NACA 6-series airfoils. All tests, were conducted at a chord Reynolds number of 8×〖10〗^5, and for a range of angle of attack -2 to14 degree. Generation of Wing tip vortices are eliminated by placing an End-plate on the wing tip. Static pressure distributions over the upper surface of the wing at three chordwise direction and at one spanwise direction along the quarter chord line are obtained. The results show that the sweep angle has significnt effect on the surface pressure distribution at different chrdwise sections. In addition, by eliminating the wing tip vortices, the pressure near the wing tip area decreases. As the wing sweep angle increases, the pressure along the wing chordwise sections increases and formation of the laminar separation bubble near the leading edge takes place at higher angles of attack
Keywords:
Wind Tunnel ; Swept Wing ; Pressure Distribution ; Sweep Angle ; Wing Tip Vortex

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