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Effect of Geometric Distortion on the Flow Field and Performance of an Axisymmetric Supersonic Inlet

Akbarzadeh, Hossein | 2021

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 53942 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Farahani, Mohammad
  7. Abstract:
  8. Inlets must decelerate the air with lowest loss and drag together with a given pressure and Mach number with best quality and uniformity to the engine. This is done based on flight Mach number, by an arrangement of shock waves and surfaces gradient in the inlet. Any distortion in the flow field and the inlet geometry parameters may disrupt such arrangement and influence on the inlet performance, in addition, under critical conditions, it might affect the stability of the intakes. Any distortion in the flow field and the inlet geometry parameters may disrupt such arrangement and influence on the inlet performance, in addition, under critical conditions, it might affect the stability of the intakes. This study aims to investigate the effects of geometric distortions created on the spike surface on the main flow field characteristics of an inlet. Thus, some numerical simulations have been conducted for air flow in an axisymmetic inlet. Initially the accuracy of simulation results was compared with experimental ones for the clean geometry. After validation of the numerical predictions, a distortion has been added to simulation. The effects of position and geometry of the distortion were then studied on the performance parameters of the inlet. The position and the size of the distortion showed the considerable effect on the arrangement of shock waves in front of the inlet and also different pressure loss and drag obtained depending on locating the distortion in upstream or downstream of normal shock wave
  9. Keywords:
  10. Numerical Simulation ; Performance Parameter ; Supersonic Flow ; Geometric Distortion ; Axisymmetric Supersonic Inlet

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