Abstract
NASA LS (1)-0417 is an airfoil profile widely used in vehicle design especially in aircrafts for subsonic and transonic speed regimes. Performance of the airfoil is mainly determined by stall aerodynamic characteristics during flight. Further increase in stalling angle of the airfoil, the engineers adopts a single or multiple flaps in the trailing edge region of the main airfoil. The present study deals with a new attempt to achieve the post-stall or increased lift characteristics of NASA LS (1)-0417 airfoil beyond the stalling angle. The airfoil’s surface parts are subjected to allow the air to flow freely over and into the airfoil with increase in lift. The modified airfoil is designed from the base airfoil using the commercial design software and imported to the computational domain with boundaries around the model and meshed properly for solving the problem using the analysis software. The aerodynamic characteristics are compared with the baseline NASA LS (1)-0417 airfoil.
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