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Passenger Aircrafts Wing Sections Optimization Using Shock Control Bump

Chaharlang Kiani, Kiarash | 2012

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 43623 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Mazaheri, Karim
  7. Abstract:
  8. The development of the boundary layer and shock boundary layer interaction essentialy determine the performance boundaries of transonic aircrafts. Employing shock and boundary layer control has therefore a large potential for improving flight performance. Aerodynamic surfaces of these aircrafts usually have very closed design points and critical points so small changes in angle of attack and free stream mach number cause entering drag divergence. Adaptive wings are the aerodynamic surfaces that use additional devices to control the flow pattern for improvment of aerodynamic performance in different flight conditions. Shock Control Bump is a control mechanism that is used for shock wave weakenning. This control mechanism avoids the rapid increase of drag coefficient by geometrical adaptation of airfoil, according to current flight conditions. The region of the airfoil to be adapted can be restricted to a small zone with small height and this geometrical adaptation results in lower wave drag. parametric research on Shock Control Bump and numerical optimization of Shock Control Bump for RAE 2822 and NACA 64A010 airfoils are the main purposes of this thesis and shape optimization for an adaptive bump were carried out for different mach numbers.For present investigatons Differential Evolution Algorithm were used. Simple fomulation, easy parallelization, few control variables and vectorial nature to steer the minimization are the advantages of this method that make it appropriate for engineering optimization problems specially for aerodynamics.
  9. Keywords:
  10. Drag Reduction ; Transonic Flow ; Optimization ; Differential Evolution Algorithm ; Shock Control Bump

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