A numerical method which simulates the transonic flow around an aircraft and its engines is described. The method solves the transonic potential equations by a finite element technique with automatic mesh generation. The nacelle can be either flow-through or powered with specified inlet conditions. In the latter case the plume is solid. Results for an isolated nacelle and for a complete wing-fuselage-nacelle configuration are shown.
Calculation of Transonic Flows around an Aircraft Configuration with Motorized Nacelle
1985
11 pages
Report
No indication
English
Computation of Transonic Flows with Nacelle Simulation
NTIS | 1987
|Accelerated iterative calculation of transonic nacelle flowfields
Tema Archive | 1976
|