Abstract
According to the objectivity of UAV helicopter, endurance is a valuable performance. To increase the endurance, we need to decrease the helicopter required power. Within the research scope in vertical movement only, 5 parameters of blades planform design were considered as design variables. They are root chord of the blades, taper location, taper ratio, pitch angle, and tip twist angle. Optimization was done using own developed genetic algorithm codes with built-in blade element momentum theory (BEMT) as a performance calculator. It was chosen due to its ability to estimate rotor performance quickly. Several CFD simulation were done to reduce the error of blade element momentum theory calculation. Using constant adjustment methods, BEMT can predict thrust and power with a difference with respect to CFD of 3.8% and 8.2% respectively. The optimization result gives the optimum blades design with improving almost 11% in efficiency which came out from 9.4% reduction in power required which is good for helicopter performance.
Highlights
IntroductionThe best planform of the rotor blades must be chosen according to optimize the rotor performance [1]
In preliminary design step, the best planform of the rotor blades must be chosen according to optimize the rotor performance [1]
Researchers optimize the performance of rotor by selecting the best shape of the blade using integrated analytical programs or numerical like CFD
Summary
The best planform of the rotor blades must be chosen according to optimize the rotor performance [1]. Researchers optimize the performance of rotor by selecting the best shape of the blade (airfoil shape and blade planform) using integrated analytical programs or numerical like CFD. Analytical calculation was chosen due to the need of quick optimization in preliminary design phase [2]. The air flew through the rotor-blades generate lift and drag, which results thrust and torque acting on the rotor [3]. Performance of the rotor mostly defined by three quantities, i.e. thrust, torque or power required, and aerodynamic efficiency. It is convenient to express thrust and power required in terms of non-dimensional quantities so called thrust coefficient and power coefficient which expressed as follows
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