Effect of Reynolds number on the thrust generation of a pitching Prandtl-D root-ns foil

The Prandtl-D root-ns (NASA Preliminary Research Aerodynamic Design to Lower Drag) foil inspired from flight of birds, designed by NASA is intended to develop future low drag foils. The flow around a Prandtl-D root-ns foil pitching about its quarter chord point is studied numerically using Ansys-Fluent. The objective is to understand the effect of variation in Reynolds number on the thrust generation of a Prandtl-D root-ns foil. Numerical simulations are conducted over a range of Reynolds numbers, Re $=$ 200 - 2000, for~various Strouhal numbers at a pitching amplitude of $5^{o}$. In order to further test the thrust generation performance of Prandtl-D root foil, the obtained results are compared with NACA (National Advisory Committee for Aeronautics) series foil NACA0012. The Prandtl-D root-ns foil is observed to perform better compared to NACA0012 foil, in terms of thrust generation. The reduction in viscous component of drag for the Prandtl-D root-ns foil compared to NACA0012 foil is responsible for enhancement in thrust generation. The results of the present study will help to design high performance under water vehicles.