The objectives of this investigation have been to design a variable camber system, establish its performance capabilities and provide data to support a decision for flight demonstration. This report describes the structural loads and stress calculations. The variable camber wing consists of leading and trailing edge flaps that can be deflected to match the camber requirements of any flight condition. Wing leading and trailing edge flaps with flexible skins, combined with a simple internal mechanism, are used to achieve smoothly curved upper surfaces so that an optimum wing shape can be provided throughout the flight spectrum.
Loads Report Variable Camber Wing - Phase I
1973
358 pages
Report
No indication
English
Aircraft , Fluid Mechanics , Wings , Jet fighters , Variable incidence wings , Leading edge flaps , Camber , Leading edges , Trailing edge , Skin(General) , Performance(Engineering) , Loads(Forces) , Structures , Stresses , Safety , Weight , Strength , Geometry , Velocity , Maneuverability , Gust loads , Gusts , Fuselages , Flexible structures , Supersonic flight , Advanced technology variable camber wing , Variable camber wings , F-8 aircraft , Design , Finite element analysis , ATVCW(Advanced technology variable camber wing)
NTIS | 1973
NTIS | 1973
Summary Technical Report Variable Camber Wing - Phase I
NTIS | 1973
|NTIS | 1973
Additional Studies, Variable Camber Wing - Phase I
NTIS | 1974
|