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Numerical and Experimental Investigation of Supersonic Flow in an Axisymmetric Inlet

Sepahi Younsi, Javad | 2009

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 39879 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Soltani, Mohammad Reza
  7. Abstract:
  8. No considerable investigation of inlet aerodynamics has been done in our country up to now. Some numerical study in this field has been accomplished without any experimental test. To solve the inner and outer flow field of the inlet in this investigation, the numerical methods has been used and also experimental tests for code validation has been done. The inlet is an axisymmetric external compression one. In the numerical simulation the Navier-Stokes equations with explicit finite volume method have been used to model the axisymmetric, steady and turbulent flow field of the inlet in a structured grid. Viscous fluxes with a finite volume method, molecular viscosity coefficient with the Sutherland law and turbulent viscosity coefficient with the Baldwin-Lomax algebraic model have been computed. To compute the convective fluxes the Roe scheme and new schemes, AUSM+-up for all speed and AUSMPW, have been used to study the performance of new schemes and compare them with the Roe scheme. The original version of AUSMPW scheme has serious problems connected to the stability and accuracy. In this investigation for the first time some modifications inspired from the AUSM+-up for all speed scheme have been done in the original version of AUSMPW scheme that result in better stability and accuracy. To improve the spatial discretization accuracy the MUSCL approach has been used. Also wind tunnel tests have been done and for three flow patterns in five locations experimental data (static and total pressure) are obtained. Results show that the numerical code can capture the experimental data with acceptable level of accuracy. The Roe scheme has the highest accuracy and the AUSM+-up for all speed scheme is most efficient. The AUSMPW scheme has stability problems in some situations and its accuracy is low
  9. Keywords:
  10. Supersonic Intake ; Roe Method ; Baldwin-Lomax-Smagorinsky (BLS)Turbulence Model ; Convective Flow ; Advection Upwind Splitting Method (AUSM) ; Muscl Method ; Advection Upstream Splitting Method by Pressure Based Weight Function (AUSMPW)

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