Experimental Investigation of the Effects of Wing Aspect ratio and its distance from the Tail on the Aerodynamic parameters at high A.O.A

Afshari, Abbas | 2008

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 39166 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Soltani, Mohammad Reza; Hejranfar, Kazem
  7. Abstract:
  8. In recent years, requirement to increase projectile performance, leads to a great interest in high angle of attack Aerodynamics. Projectile Maneuverability is a concept which is defined by having the capability to perform at high angles of attack while maintaining attached flow over the tail, rather than a capability of performing a mission in minimum possible duration. Interaction between body, wing and tail vortices can delay vortex breakdown over the wing and as a result may enhance projectile maneuverability. Studies show that wing aspect ratio and tail location have a remarkable influence on the vortices interaction and thus projectile maneuverability. In the present study, a series of experiments are carried out on a body-wing-tail configuration to investigate their interferences. A projectile model was designed with the capabilities of placing horizontal tail at various locations and installing wings with different aspect ratios. Six-component balance was used to measure the aerodynamic forces and moments. Flow visualization was performed by tuft and oil in order to gain an insight into the corresponding flow field. Results show that, reducing wing and tail distances, increases lift and decreases drag at high angles of attack. In addition to our intensive experiment, FLUENT was used to obtain similar data. Our FLUENT results show that up to 20 degrees A.O.A the data compares well with the experimental ones. However, at high angle of attack, the deviation is significant
  9. Keywords:
  10. Delta Wing ; Vortex Flow (Eddy Current) ; Tailcontrol Projectile ; Vortex Interaction

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