MEASUREMENTS ON AN OSCILLATING 70-DEG DELTA-WING IN SUBSONIC FLOW

A series of low-speed wind tunnel tests on a 70-deg sharp leading-edged delta wing at both static and dynamic ons were performed to investigate the aerodynamic forces and moments. Forces and moments were obtained from a six-component internal strain-gauge balance. Large amplitude dynamic motion was produced by sinusoidally oscillating the model over a range of reduced frequencies. Static results compared well with previous experimental findings. Significant Reynolds number effects were present in the experimental measurements. Reynolds number effects are reduced, but still present when a sharper leading-edge delta wing was tested. Large hysteresis loops and a delay in dynamic stall were seen in the dynamic data. Dynamic forces and moments were a strong function of reduced frequency. Nonzero sideslip created complex rolling moment and lift behavior due to asymmetric vortex bursting. © 1989 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.