The effects or nonaxisymmetrical fuselage design for reducing the drag of a low-sonic-boom airplane an investigated by computational fluid dynamics (CFD) analyses and verified in wind-tunnel tests. The nonaxisymmetrical fuselage design, in which the upper side of a fuselage is designed for low drag whereas the lower side is designed for low sink boom, is applied to the design of a Mach 1.7 scaled supersonic experimental airplane. The designed airplane is compared with a low-drag airplane and a low-sonic-boom airplane with an nonaxisymmetrical fuselage. The CFD analyses show the nonaxisymmetrical fuselage design can significantly reduce the drag of a low-sonic-boom airplane with an axisymmetrical fuselage without losing its low-sonic-boom characteristics. The CFD results are verified by force and near-field pressure measurements in supersonic wind-tunnel tests.
Nonaxisymmetrical fuselage shape modification for drag reduction of low-sonic-boom airplane
Simultane Reduzierung des Strömungswiderstandes und des Überschallknalls durch eine asymmetrische Form des Flugzeugrumpfs
AIAA Journal ; 41 , 8 ; 1413-1420
2003
8 Seiten, 18 Bilder, 2 Tabellen, 10 Quellen
Aufsatz (Zeitschrift)
Englisch
NON-AXISYMMETRICAL FUSELAGE SHAPE MODIFICATION FOR DRAG REDUCTION OF A LOW SONIC-BOOM AIRPLANE
British Library Conference Proceedings | 2003
|Airplane Configurations for Low Sonic Boom
NTRS | 1971
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