OPPAV 천이 기동 영역의 틸트 프롭 공력 해석

Abstract

The aerodynamic characteristics of a three-bladed prop were investigated along the tilt angle in the transition maneuver from hover to forward flight using computational fluid dynamics methodology. According to the change of the forward speed and the collective pitch angle at each tilt angle, it was confirmed that small changes in the two parameters had a linear relationship with the aerodynamic characteristics. Along the transition maneuver line, prop thrust continued to decrease, and torque showed a tendency to decrease initially and increase gradually. It was also confirmed that the hovering efficiency decreased but the propulsive efficiency increased as the forward speed was increased and the prop was changed from the rotorcraft mode to the airplane mode. It was found that the convection of the tip vortex and the wake showed asymmetry and inclination, and the surface pressure of the prop blade appeared asymmetrically due to the different aerodynamic environment by the inflow change except for the tilt angle of 0 degrees and 90 degrees. The aerodynamic characteristics of oscillating at 3/rev during one rotation of the prop was shown and The peak-to-peak value of the oscillating aerodynamic force was maximum at the tilt angle of 60 degrees.