Experimental Test Campaign for Stall Characterization on a Generic Variable Sweep Wing

Aircraft wing stall is a highly complex phenomenon as several mechanisms interact depending on global and local flow characteristics. Recent developments in numerical methods and aerodynamic modeling make possible the vision of an accurate prediction of stall in the near future. In order to reach this objective, there is a need for a high-quality experimental database for validation, including surface and flowfield measurements. To that purpose, a generic test model was specifically designed and built to provide force balance metrics as well as steady and unsteady pressure signals. In particular, the model takes into account forward, backward, and zero sweep angles while adding high-lift devices in order to modify the stall mechanism on the wing. The model was then tested at the ONERA-F2 wind tunnel, and experimental results validate the model’s intended stall characteristics and provide the needed flow data for future numerical validations. This paper describes the different design choices, the measurement techniques considered for this test campaign, and the first results obtained validating the stall processes expected for the different designed configurations.