Slender delta wing planforms are susceptible to self-induced roll oscillations due to aerodynamic hysteresis during the limit cycle roll oscillation. Test results are presented which clearly establish that the static rolling moment hysteresis has a damping character; hysteresis tends to be greater when, due to either wing roll or side slip, the vortex burst moves back and forth over the wing trailing edge. These data are an indirect indication of the damping role of the vortex burst during limit cycle roll oscillations.
Static measurements of slender delta wing rolling moment hysteresis
Journal of Aircraft ; 28
1991-04-01
Miscellaneous
No indication
English
Analysis of Wing Rock Due to Rolling-Moment Hysteresis
Online Contents | 2008
|Analysis of Wing Rock Due to Rolling Moment Hysteresis
AIAA | 2008
|