Abstract
Euler solutions around the Swedish fighter airplane, JAS 39 Gripen are presented. A patched multiblock grid with nine blocks is generated by transfinite interpolation. The full Euler equations are discretized in space by a centered finite volume method and integrated in time using an explicit four-stage Runge-Kutta scheme. It is shown that the external flow around the aircraft is significantly affected by the interaction with the internal flow. The problem with boundary conditions at the inlet of the air intake and at the exit of the exhaust nozzle is discussed. A method of how to apply characteristic boundary conditions is presented. Solutions with different boundary conditions at the artificial boundaries are compared. (A)
| Original language | English |
|---|---|
| Title of host publication | Unknown Host Publication Title |
| Publisher | New York, USA, American Society of Mechanical Engineers |
| ISBN (Print) | 0791805840, 9780791805848 |
| Publication status | Published - 1991 |
ASJC Scopus subject areas
- General Engineering