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Effect of Delta Wing Leading Edge Vortex on Pressure Distribution of Fuselagein in Subsonic Regime

Sadri, Vahid | 2012

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 42912 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Soltani, Mohammad Reza; Ghorbanian, Kaveh
  7. Abstract:
  8. The delta wing has proven to be very useful for the study and understanding of the basic features of separation-induced vortex flows since many aspects of these vortex flows can be generated with this simple shape. A phenomenon of special importance to vortical flows is vortex breakdown. Vortex breakdown remains an important and complicated phenomenon that can have negative or positive effects. The delta wing leading edge vortex is emphases in many experiments. Most of these experiments are focused on the delta wing only.In this research, emphasis is on vortex interaction of delta wing-canard-fuselage configuration. A series of low speed wind tunnel tests were carried out to investigate vortex interaction in delta wing-fuselage configurations. These studies are conducted with the presence of body in a wide range of angles of attack. Our data show that canard plays a significant role in maintaining vortical flow and delaying vortex breakdown phenomenon over the wing surface, particularly at high angles of attack. Fuselage and wing vortex interactions dominate the whole flowfield. By frequency domain analysis on canard, delta wing and fuselage, interaction of vortex with these components explained. Spectrum analysis shows that canard increases the frequency and amplitude of delta wing vortex. In addition, existence of body and canard delay the vortex breakdown on the delta wing.
  9. Keywords:
  10. Delta Wing ; Wind Tunnel ; Frequency Analysis ; Vortex Flow (Eddy Current) ; Vortex Breakdown ; Fuselage

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