悬停状态共轴刚性旋翼机身气动干扰特性

doi:10.7527/S1000-6893.2023.29284

Abstract

Abstract:

Experimental and computation studies were conducted on the aerodynamic interaction between coaxial rigid rotor-fuselage in hover. The influence of fuselage aerodynamic interference in hover on the aerodynamic characteristics of coaxial rigid rotor and the pressure distribution on the fuselage surface was analyzed. It is found that the range of high lift areas at the tip of the upper and lower rotor blades is increased， and the power coefficient of the rotors is reduced at the same tension coefficient with the aerodynamic interaction of the fuselage. The rotor maximum Figure of Merit （FM） increases by approximately 4.6%. The fuselage generates vertical down-load， which is about 7% of the rotor pull force， with the influence of rotor downwash flow. Excluding vertical down-load on the fuselage， the maximum FM of the rotor is reduced by about 6% compared to isolated rotors. Under the aerodynamic interaction of rotor， the fuselage generates an upward force moment， which is proportional to the rotor tension coefficient. The surface pressure of the fuselage exhibits an unsteady variation of 4 times the rotational frequency.

Key words: coaxial rigid rotor, aerodynamic interaction, fuselage, wind tunnel test, hover

CLC Number:

V211.52

Pengpeng SUN, Ping’an LIU, Feng FAN, Wei ZENG. Aerodynamic interaction characteristics of coaxial rigid rotor⁃fuselage in hover condition[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529284-529284.

Figures/Tables 19

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名称	要求
机身尺寸/m	长4.16 宽0.71 高0.79
桨毂形式	刚性无铰式
模型旋翼直径	4 m
桨叶片数	上、下旋翼各4片
旋翼旋转方向	上旋翼逆时针、下旋翼顺时针（俯视）
额定转速	907 r/min
上、下旋翼间距	0.14R

状态	总距
上、下旋翼同总距试验	0°，3°，5°，6°，7°，8°，9°，10°，11°，12°
下旋翼扭矩配平试验	上旋翼总距为7°，8°，9°，10°；下旋翼总距根据上旋翼扭矩配平确定

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Aerodynamic interaction characteristics of coaxial rigid rotor⁃fuselage in hover condition

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