Aerodynamic optimization of a propeller airfoil at low Reynolds numbers

The aerodynamic optimization method was presented to design a propeller airfoil for stratosphere airship at low Reynolds numbers. delta class and shape transformation were adopted describe the geometry as variables. flow field calculated by an open-source code XFOIL obtain characteristics targets. separated particle swarm employed algorithm. case started with typical number E387 obtained thicker more cambered using proposed method. fields of optimized initial airfoils analysed CFD. Results suggested that lift-to-drag ratio changed from 35.7 45.9 increasing rate 28.5% cruise condition. overall performance has been significantly improved both off-design conditions within wide range attack angle. platform here is efficient effective low-Reynolds-number designs.