Some typical effects of static aeroelastic correction factors in context with the definition of structural design loads for major aircraft components are discussed. The influences on response parameters and resulting design loads are shown as well as the aeroelastic optimization of trailing edge flaps with respect to geometry, efficiency, and hingemoments.
Static Aeroelastic Considerations in the Definition of Design Loads for Fighter Airplanes
1987
20 pages
Report
Keine Angabe
Englisch