The application of combined momentum and blade element theory for aerodynamics performance analysis of rotating blades

Computer code for performance aerodynamics analysis of three types of rotating blade configuration had been successfully developed. The computer code which developed based on the combined Momentum and Blade Element Theory can be applied for Horizontal axis wind turbine performance analysis, rotor blade helicopter in vertical climb and forward flight and the aircraft propeller analysis. The Combined Momentum and Blade Element Theory required the detailed blade geometry involves the chord and twist angle distribution along blade span and also the aerodynamics characteristics of its airfoil section. The developed computer code allows one to obtain the detail of differential thrust coefficient, differential torque coefficient and differential power coefficient along blade span. Integrate those differential quantities will give the thrust coefficient, torque and power coefficients. The comparison result with other method or experimental result were not yet be done due to difficulties in obtaining suitable data for such purposes. Hence the comparison result with other method has been suggested for the future work.