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Experimental investigation of Pressure Distribution over Delta Wing in
Sub/supersonic Speed

Sadeghian, Saeed | 2017

1994 Viewed
  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 49725 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Soltani, Mohammad Reza
  7. Abstract:
  8. Flow characteristics analysis over a wing, is one of the pioneer challenges in super and sub-sonic flow near flying objects. Taking into account of growing rate of low aspect ratio utilization, usually called Delta wings, investigation of vortex behavior over this wings is highly noticeable. In addition, the lack of research in this branch of Aerodynamics inside the country, considering it’s critical application, has doubled the importance of doing research in this filled. Experimental researches on super-sonic flow over a Delta wing is limited and there are not much accurate researches about vortexes in this category of wings. In this work, the main effort is to investigate the phenomena in a higher level of accuracy, considering all challenges in this field. Wing will be in different situations when exposed to different flight scenarios. In this regards, physical investigation of vortex behavior and their influence on Delta wing are among main goals of present work. In this regards, a half-body model was utilized in a way that Delta wing was joined to a body having a nose. The main principle of this research was based on pressure. Pressure data were gathered using pressure sensors which were connected to wholes implemented to model. Finally, having pressure distribution over the wing, flow characteristics analysis was performed. Investigations showed that vortex core is going toward the root of the wing by increasing the angle of attack and also the explosion location gets closer to the tip. Vortex pressure factor increase with Mach number grows andin super-sonic Machnumber leading edge becomessonic. Inaddition, experimental observations showed that with vortex pressure factor getting more negative with angle of attack, in comparison with potential flow created has faster rate
  9. Keywords:
  10. Delta Wing ; Subsonic Flow ; Supersonic Flow ; Pressure Distribution ; Vortex Flow (Eddy Current) ; Wind Tunnel

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