A generic, transonic, supercritical, low aspect-ratio wing was tested at design incidence of 5 deg at Mach numbers from 0.25 to 0.96. Oil-flow studies at the design Mach number of 0.85 showed local-flow separation, which, in retrospect, might have been avoided. At Mach 0.82 with unseparated flow, the surface-flow angles were less than 10 deg. Predictions with the FLO22 transonic potential code are good. Lift interference is strong without tunnel-wall suction. Evidence from this study shows that wings that are optimized for mild shock waves and pressure-recovery gradients generally have small, three-dimensional flow at conditions for unseparated flow.
Computational-experimental pressure distributions on a transonic, low-aspect-ratio wing
1984-01-01
Conference paper
No indication
English
Transonic low aspect ratio wing-winglet designs
AIAA | 1988
|Transonic low aspect ratio wing-winglet designs
NTRS | 1988
|