Aerodynamic effect analysis of rotor downwash on wings of composite high-speed helicopter

Abstract

The analysis of the aerodynamic interference of the downwash on wings under different intensities on both sides of the rotor of the composite high-speed helicopter, can provide a certain reference for the design and optimization of the aerodynamic shape of the similar configuration helicopter.The unsteady momentum source method is used to perform the numerical simulation of the flow field of a composite high-speed helicopter in hovering and forward flight states, and the aerodynamic effects of different downwash on both sides of the rotor on wings are analyzed.The effect of aerodynamic characteristics on changing the height of the rotor disc and the aspect ratio of wing is studied.The results show that, when the composite high-speed helicopter flies forward, the peak lift difference between the two sides of the wing is decreased with the increase of the rotor disc height, and the peak value falls at a lower speed.With the increase of the wing aspect ratio, the peak lift difference between the two sides is decreased.Under the condition of same speed after the peak value, the slender the wing is, the smaller the lift difference between the two sides is.

Keywords

• momentum source
• composite high-speed helicopter
• rotor
• wing
• aerodynamic characteristics