| タイトル | Computational analysis of methods for reduction of induced drag |
| 著者（英） | Cave, Chris; Janus, J. M.; Chatterjee, Animesh |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1993-01-01 |
| 言語 | eng |
| 内容記述 | The purpose of this effort was to perform a computational flow analysis of a design concept centered around induced drag reduction and tip-vortex energy recovery. The flow model solves the unsteady three-dimensional Euler equations, discretized as a finite-volume method, utilizing a high-resolution approximate Riemann solver for cell interface flux definitions. The numerical scheme is an approximately-factored block LU implicit Newton iterative-refinement method. Multiblock domain decomposition is used to partition the field into an ordered arrangement of blocks. Three configurations are analyzed: a baseline fuselage-wing, a fuselage-wing-nacelle, and a fuselage-wing-nacelle-propfan. Aerodynamic force coefficients, propfan performance coefficients, and flowfield maps are used to qualitatively access design efficacy. Where appropriate, comparisons are made with available experimental data. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 93A25536
AIAA PAPER 93-0524 |
| 権利 | Copyright |
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