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Computational Simulation of Supersonic Flow in an Axisymmetric Mixed Compression Inlet

Zarea Chavoshi, Majid | 2015

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 47777 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Tayyebi Rahni, Mohammad; Ebrahimi, Abbas
  7. Abstract:
  8. Inlet performance is an important field in aerodynamic design of aerial vehicle engines. This study has been focused on nummerical investigation of inlet performance. For this purpose, a density based finite volume CFD code has been developed to solve supersonic axisymmetric flow in a mixed compression inlet. A structured multi-block grid and an explicit time discritization of Reynolds averaged Navier-Stokes (RANS) equations have been used. Furthermore, both Roe’s approximated Riemann solver and advection upwind splitting method (AUSM) have been utilized for computing inviscid flux vectors. Also, the monotone upstream centered schemes for conservation laws (MUSCL) extrapolation with Van Albada limiter has been used to obtain second order accuracy. In addition, Spalart-Allmaras one-equation turbulence model has been used to close the governing equations. An important outcome of the present work is implementation of modified Spalart-Allmaras turbulence model for more accurate prediction of shock/boundary layer interaction. Finally, the code has been utilized for nummerically simulation of a specific supersonic mixed compression inlet. The effects of exit blockage ratio (EBR), free stream Mach number, and Reynolds number on performance parameters, including drag, total pressure recovery (TPR), mass flow ratio (MFR), and flow distorsion (FD) have been discused and investigated. Results show that Reynolds number does not have a large effect on performance parameters, while both Mach number and exit blockage ratio effects are significant
  9. Keywords:
  10. Mixed Compression Supersonic Intake ; Spalart-Almaras Turbulence Model ; Roe Upwind Scheme ; Advection Upwind Splitting Method (AUSM) ; Supersonic Axisymmetric Flow ; Multiblock Grid

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