Experimental study of shockwave formation patterns over an airfoil on laminar flow and its relationship with boundary layer transition

Resumo

© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.A detailed investigation of the shock wave formation patterns over a NACA0012 airfoil in a mostly laminar, transonic regime is presented. Information regarding the position of the boundary layer transition was obtained using Temperature Sensitive Paint (TSP) for similar conditions previously studied using Pressure Sensitive Paint (PSP). In this paper, previous results regarding shockwave formation patterns are revisited and further analyzed with the additional input of TSP data. Results indicate a strong correlation between the position of the boundary layer transition and the shockwave onset, confirming the hypothesis proposed in the previous investigation. Thus, the process of shockwave formation and the role of boundary layer interaction in it is further clarified. Besides Pressure and Temperature Sensitive Paints, the traditional method of pressure taps was used to confirm PSP measurements and account for possible deviations.