FUSELAGE SHAPE OPTIMIZATION AIMED AT WING-FUSELAGE CONFIGURATION DRAG REDUCTION AT SUPERSONIC SPEEDS
The problem of fuselage shape optimization of the wing-body configuration is considered in the following three formulations. In the first one, the angle of attack is fixed and equal to zero, the wing has a symmetric airfoil, and the fuselage is based on circular cross sections. In the second one, th...
Gespeichert in:
| Hauptverfasser: | , |
|---|---|
| Format: | Artikel |
| Sprache: | Russisch |
| Veröffentlicht: |
Moscow State Technical University of Civil Aviation
2017-01-01
|
| Schriftenreihe: | Научный вестник МГТУ ГА |
| Schlagworte: | |
| Online-Zugang: | https://avia.mstuca.ru/jour/article/view/992 |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|