機体重量によるコンパウンドヘリコプタの空力性能への影響

抄録

This paper investigates the flight performance of a compound helicopter with varying gross weight and advance ratio through high-fidelity CFD simulations. The compound helicopter configuration studied here consists of a single main rotor used on UH-60A helicopter and a wing-body designed by JAXA (Japan Aerospace Exploration Agency) as the conceptual model of a compound helicopter. The empennage, anti-torque rotor and other details are omitted for simplicity. The gross weight changes from 60% to 110% of the maximum gross weight of UH-60A. The advance ratio varies from 0.1 to 0.8. As the results, the net effective lift to drag ratio of the aircraft decreases rapidly at high advance ratios and overweight (110%) because of increasing magnitude of aerodynamic interaction between the main rotor and the wing-body. The collective pitch and longitudinal cyclic pitch angles are also influenced significantly as the gross weight increases. When the gross weight is 1.1 times of that of the UH-60A, the net required power increases to 1.3 times compared to the net required power when the rotor/wing-body aerodynamic interaction is not considered.