Aerodynamic Interactions Between a Rotor and Wing in Hover

Felker, Fort F.; Light, Jeffrey S.

doi:10.4050/jahs.33.53

Cited by 39 publications

(12 citation statements)

References 1 publication

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“…8) and changes the rotor performance with respect to the isolated case (Ref. 9). In this operating condition, the rotor wake strikes the upper surface of the wing and generates a complex three-dimensional unsteady flow, which negatively affects the aircraft performance (Ref.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Interaction between Rotor and Tilting Wing in Hovering Flight Condition

Droandi¹,

Zanotti²,

Gibertini³

2015

j am helicopter soc

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The hovering performance and the lifting capability of tiltrotor aircraft are strongly affected by the aerodynamic interaction between wing and rotors. The tiltwing concept represents an interesting technology to increase the hover performance by reducing the wing-rotor interference. The present work investigates the aerodynamic interaction between wing and rotor in hover for a scaled tiltwing aircraft half-span model. A comprehensive experimental campaign, including force measurements and particle image velocimetry surveys, was performed together with computational fluid dynamics simulations. Numerical predictions were validated using experimental data and were used to describe the flow field. Nomenclature

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Section: Introductionmentioning

confidence: 99%

Aerodynamic Interaction between Rotor and Tilting Wing in Hovering Flight Condition

Droandi¹,

Zanotti²,

Gibertini³

2015

j am helicopter soc

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“…Previous studies on tilt rotors have shown that the rotor downwash velocity profile has significant effects on the measured download on the aircraft (Refs. 13,15). Therefore, measurements of the downwash velocities of an isolated rotor at different radial locations were obtained using a hot wire probe at an axial distance of 0.21D below the rotor plane, corresponding to the wing location on the installed rotor.…”

Section: Isolated Rotor Wake Velocimetrymentioning

confidence: 94%

An Experimental Investigation of Ground Effect on a Quad Tilt Rotor in Hover

Mylapore¹,

Schmitz²

2015

j am helicopter soc

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The performance of a 0.031 geometrically scaled fuselage/wing model of a Quad Tilt Rotor (QTR) operating in helicopter mode while hovering in-ground effect (IGE) and out-of-ground effect (OGE) was experimentally studied. The effect of ground proximity was tested by varying the height of the model above the ground. Measurements included download on the airframe; thrust, torque, and rpm of the rotors; and static pressures along the centerline of the bottom of the fuselage. Fixedpitch propellers were used to model the rotors. The downwash distributions of the rotors were measured and compared well with large-scale V-22 rotor measurements. Tuft flow visualization was used to identify the physical processes causing changes in the download and static pressure measurements. The uncertainty of the measured quantities was determined to 95% confidence levels. A significant download (9 ± 0.5% of the rotor thrust) was observed in hover, OGE. The download reduced substantially IGE and become an upload (8.5 ± 0.5% of the rotor thrust) when the wheels of the QTR were on the ground. Flow visualization and pressure measurements suggest that the upload IGE is caused by the interaction of the wakes from the four rotors that are turned parallel to the ground and meet under the fuselage. The measured download, coupled with power measurements, indicate that for a given power the available vehicle thrust significantly increases IGE.

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“…This problem of aerodynamic download was encountered in the development of the tilt-rotor and the use of flaps was shown the ameliorate the wing download in low speed flight [46]. It is likely that a winged compound helicopter would also implement the use of flaps although the weight penalty of the wing would also have to be considered.…”

Section: Hover Ceilingsmentioning

confidence: 99%

Performance comparison between a conventional helicopter and compound helicopter configurations

Ferguson

Thomson

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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The compound helicopter is a high speed design concept that is once again being explored due to emerging requirements for rotorcraft to obtain speeds that significantly surpass the conventional helicopter. This increase in speed, provided efficient hover capability is maintained, would make the compound helicopter suitable for various roles and missions in both military and civil markets. The aim of this paper is to investigate the compounding of the conventional helicopter and how the addition of thrust and wing compounding influences the performance of this aircraft class. The paper features two compound helicopters. The first configuration features a coaxial rotor with a pusher propeller providing additional axial thrust, and is referred to as the coaxial compound helicopter. The second configuration, known as the hybrid compound helicopter, features a wing and two propellers providing thrust compounding. In this study, the performance of these two compound helicopter configurations are assessed and compared with a conventional configuration. The paper presents the standard performance parameters of each configuration which include the power required in steady level flight, the maximum range, the maximum endurance and the hover ceiling of each of the aircraft configurations. Furthermore, a performance analysis of each configuration flying standard helicopter missions is conducted. The results of the hybrid configuration show that the addition of the wing to the design successfully offloads the main rotor at high speeds, however significant propulsive power is required by the propellers to overcome the airframe drag. Concerning the coaxial configuration, the power required by the coaxial compound and baseline configurations are comparable at low speeds.However, in high speed flight a significant amount of power is required by the propeller to divorce the coaxial rotor of its propulsive duties. The results also reinforce the importance of reducing airframe drag in a potential compound helicopter design.*Manuscript accepted for publication in the Journal of Aerospace Engineering KeywordsCompound helicopter, Rotorcraft and performance.

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Aerodynamic Interactions Between a Rotor and Wing in Hover

Cited by 39 publications

References 1 publication

Aerodynamic Interaction between Rotor and Tilting Wing in Hovering Flight Condition

Aerodynamic Interaction between Rotor and Tilting Wing in Hovering Flight Condition

An Experimental Investigation of Ground Effect on a Quad Tilt Rotor in Hover

Performance comparison between a conventional helicopter and compound helicopter configurations

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