An Explicit Finite-Difference Solution of Hypersonic Flows Using Rational Runge-Kutta Scheme

  • Nobuyuki Satofuka
  • Koji Morinishi
Conference paper

Summary

An explicit method of lines approach has been applied for solving hypersonic flows governed by the Euler, Navier-Stokes and Boltzmann equations. The method is based on a finite difference approximation to spatial derivatives and subsequent time integration using the rational Runge-Kutta scheme. Numerical results are presented for the hypersonic flow over a double ellipse which is a test case of the Workshop on Hypersonic Flows for Reentry Problems, January 22–25, 1990 in Antibes(France).

Keywords

Titan Lution Reso 

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1).
    Morinishi, K. amp; Satofuka, N., “Convergence Acceleration of Rational Runge-Kutta Scheme for Euler and Navier-Stokes Equations,” A Collection of Technical Papers ISCFD Nagoya, pp. 131–136 (1989).Google Scholar
  2. 2).
    Wambecq, A., “Rational Runge-Kutta Methods for Solving Systems of Ordinary Differential Equations,” Computing 20, pp. 333–342, (1978).CrossRefMATHMathSciNetGoogle Scholar
  3. 3).
    Jameson, A. amp; Baker, T.J., “Solution of the Euler Equations for Complex Configurations,” AIAA Paper 83 - 1929 (1983).Google Scholar
  4. 4).
    Yee, H.C., “Upwind and Symmetric Shock-Capturing Schemes,” NASA TM 89464 (1987).Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 1991

Authors and Affiliations

  • Nobuyuki Satofuka
    • 1
  • Koji Morinishi
    • 1
  1. 1.Department of Mechanical and System EngineeringKyoto Institute of TechnologyKyoto 606Japan

Personalised recommendations