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Design and Performance Optimization of a Diverterless Supersonic Inlet

Ghasemzadeh, Abolfazl | 2022

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 55164 (45)
  4. University: Sharif University of Technolog
  5. Department: Aerospace Engineering
  6. Advisor(s): Farahani, Mohammad
  7. Abstract:
  8. One of the most modern types of inlets in aircraft is the Diverterless supersonic inlet, which is used in some new UAVs and fighters, and has many advantages over other types of inlets, especially in removing the boundary layer. The most important part of DSI design is the creation of bump geometry, which requires special precision and elegance. There are various methods for designing and creating bump geometry, some of which are mentioned in this report, and finally the method of creating bump geometry is selected based on the flow around the primary cone, which is in accordance with the analytical method and is in fact the most basic and widely used method.In this study, a DSI with cowl and diffuser was designed for a fighter with a flight Mach number of 1.4 and then optimized based on the parameter of total pressure recovery. To optimize this inlet, its mouth is investigated based on the bump geometry; Because the greatest loss in total pressure occurs in the passage of shock waves, especially vertical shock waves. Numerical solutions and simulations have been performed in Ansys Fluent software and the design of experiment and optimization process has been done with the help of Design Expert software. Finally, for a more complete review, the bump optimization process, based on the geometries created in the previous section, is also repeated under Mach 2. The results show that with increasing Mach number, the optimal half-angle angle of the cone increases. Also, the optimization process in the scales of 0.5 and 0.2 in the half-angle of the cone of 20 degrees and the angle of attack of zero, has been studied and compared with the main scale. The results show that at different scales, the maximum total pressure recovery is achieved at a burial depth of 0.1 m. DSI performance has also been evaluated as stable and adequate under various conditions
  9. Keywords:
  10. Diverterless Supersonic Inlet (DSI) ; Boundary Layer ; Bumper ; Total Pressure Recovery ; Optimization ; Experiments Design ; Mach Number

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