This paper describes the current capabilities and the future plans for a three-dimensional Euler Aerodynamic Method. The basic solution algorithm is based on the finite-volume, Runge-Kutta pseudo-time-stepping scheme of FLO-57. Several modifications to improve accuracy and computational efficiency have been incorporated and others are being investigated. The computer code is used to analyze a cropped delta wing at 0. 6 Mach number and and arrow wing at 0. 85 Mach number. Computed aerodynamic parameters are compared with experimental data. In all cases, the configuration is impulsively started and no Kutta condition is applied at sharp edges.
|Original language||English (US)|
|Number of pages||19|
|Journal||NASA Conference Publication|
|State||Published - Dec 1 1986|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering