The article analyzes separation flow control on a wall-mounted hump using pneumatically enhanced or deployed actuators. Experiments were performed in the low-speed AEROLAB Educational Wind Tunnel System with a 1ft2 test section. Static pressure taps were drilled into the model as well as the bottom wall of the test section at multiple streamwise locations on the centerline. 2-D particle image velocimetry (PIV) measurements were conducted to obtain quantitative planar velocity field data. The maximum uncertainty in the u velocity was estimated to be under 1% of the freestream value. Surface flow visualization was performed using titanium dioxide suspended in baby oil as the tracer medium. Two-component PIV data were obtained for the two models. The laser sheet was aligned streamwise along the centerline of the test section, equidistant between two actuators, with the field of view starting at the location of the actuators and ending a few chord lengths downstream.
ASJC Scopus subject areas
- Aerospace Engineering