Buffeting tests were made on an aeroelastic model of a slender wing aircraft at Mach numbers of 0.2 and 0.3 and at low densities, over an angle of incidence range from 0 to 24 deg. In general the wing-root strains resembled those measured previously on an ordinary wind-tunnel model with almost the same shape. The total damping in the first and third symmetric modes was derived from tape records of the wing-root strain signal. For both modes the total damping was almost independent of the angle of incidence, even in the region of vortex breakdown. For the first mode the measured aerodynamic damping was reasonably predicted by assuming that the model was a slender delta wing with attached flow. (Author)
Some Measurements of Buffeting on an Aeroelastic Model of a Slender Wing Aircraft
1978
25 pages
Report
Keine Angabe
Englisch
Aeroelastic analysis of a slender wing
Springer Verlag | 2020
|Some static aeroelastic considerations of slender aircraft
Engineering Index Backfile | 1961
|