Experimental Study of the Wing  Sweep Angle Effect on the Pressure Distribution of a Half Model

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مطالعه تجربی اثر زاویه عقبگرد بال بر توزیع فشار روی یک نیم مدل

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 39207 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Soltani, Mohammad Reza
Abstract:
In this thesis the behavior of a 3D wing has investigated by Flow visualization and pressure acquisition test. The goal of this tests was considering changes in 3D wing section parameter in comparison with 2D airfoils. The performed Tests showed that variation in 3D wing treatment is affected by finite aspect ratio and sweep angle and also indicate changes in pressure profile, increasing pressure peak and decreasing effective speed. CFD studies has conducted to investigate special effect of sweep angle and show that lift and drag coefficient decrease with increasing sweep angle. Also different section pressure profile near the wing tip and intersection of wing/fuselage varies and miss optimum state
Keywords:
Three Dimentional Wing ; Pressure Profiles ; Sweep Angle ; Experimental Studies

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