Numerical Solution of Hypersonic Axisymmetric Flows Including Real Gas Effects Using Compact Finite-Difference Scheme

Khodadadi, Polin | 2009

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 39848 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Hejranfar, Kazem
  7. Abstract:

  8. The numerical solution of the parabolized Navier-Stokes (PNS) equations for accurate computation of hypersonic axisymmetric flowfield with real gas effects is obtained by using the fourth-order compact finite-difference method. The PNS equations in the general curvilinear coordinates are solved by using the implicit finite-difference algorithm of Beam and Warming type with a high-order compact accuracy. A shock fitting procedure is utilized in the compact PNS scheme to obtain accurate solutions in the vicinity of the shock. To stabilize the numerical solution, numerical dissipation term and filters are used. The main advantage of the present formulation is that the basic flow variables and their first and second derivatives are simultaneously computed with the fourth-order accuracy. The computations are performed for a benchmark case; hypersonic axisymmetric flow with real gas effects over a blunt cone at Mach 19.25. The present results for the flowfield variables and also their derivatives are compared with those of the second-order method. A sensitivity study is performed for the basic flowfield, including profiles and their derivatives obtained from the fourth-order compact PNS solution, and the effects of grid size and numerical dissipation used are discussed.
  9. Keywords:
  10. Blunt Body ; Hypersonic Flow ; Compact Finite Difference Method ; Real Gases ; Parabolic Navier-Stokes Equation

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