APPLICATION OF HOPOSCOTCH METHOD FOR SOLVING THE UNSTEADY TWO DIMENSIONAL, INVISCID, INTERNAL FLOWS | ||
| International Conference on Aerospace Sciences and Aviation Technology | ||
| Article 4, Volume 3, ASAT Conference 4-6 April 1989 , CAIRO, April 1989, Pages 33-42 PDF (2.2 M) | ||
| Document Type: Original Article | ||
| DOI: 10.21608/asat.1989.25862 | ||
| Author | ||
| M. M. Kemry | ||
| Associate Professor, Mech. Eng. Dept., Al-Azhar University. | ||
| Abstract | ||
| In the present study, the hoposcotch method was tested for solving the axisymmetric, inviscid, compressible, shock-free flows. The physical space was transformed into a rectangular computational space. Hoposcotch method was applied to solve the unsteady, cylindrical, conserved governing equations of motion in the transformed computational space, with the steady state solution computed as the asymptote of the transient solution. The source flow and the transonic flow through a converging-diverging nozzle were considered as test problems. The solutions were compared with the available exact, experimental, and numerical results. The method was found to be stable and in excellent agreement with the available results. An advantage of the method is that it is superior in speed (computing time); being 1.8 times faster than MacCormack's method and 2.9 to 7.3 times faster than the reference plane characteristics method. | ||
|
Statistics Article View: 167 PDF Download: 152 |
||
