Aerodynamic response of micro rotary wings in wind perturbation

Abstract In this effort, a new approach in aerodynamic modeling that accounts for unsteady wake effects as well as viscous friction drag, Leading edge suction effect and post stall behavior for rotary wings in forward flight is proposed. The adopted approach commingles the unsteadiness with the problem of helicopter rotor blade in forward flight. The results of the local normal force coefficients were compared with experimental results of the 7A rotor case study in high speed test point 312 at five non-dimensional radial positions. A CFD solver, HOST/elsA, results are compared with the obtained results at five radii locations. The results show a good agreement between the experimental results and the proposed model preserving the same pattern of variation along the azimuth angle with a slight discrepancy for amplitude and phase angle. Of particular interest, the presented model showed better agreement with the experimental for higher radii locations.

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The Future of Rotorcraft and Hovercraft

Journal of the Royal Aeronautical Society ◽

10.1017/s0001924000056426 ◽

1967 ◽

Vol 71 (673) ◽

pp. 1-8

Author(s):

Eric Mensforth

Keyword(s):

Memorial Lecture ◽

Series Production ◽

The Future ◽

Rotary Wings ◽

Sound Foundation ◽

Rotating Wing ◽

Do So

It is a privilege to pay tribute through this Cierva Memorial Lecture to a great pioneer and an honour to do so in this, the Society's Centenary Year. In 1918, when 24 years of age, Cierva designed and built a three-engined aeroplane which stalled during a turn and, after spinning, crashed. He recognised the limitations of the conventional aircraft and turned to the rotating wing.Westland's association with rotary wings began with the five-seater 600 hp Cierva C.20, built in 1934. Their first series production rotorcraft, the S.51, to the design of Igor Sikorsky, came some 14 years later. With the passage of further time, bringing some successes and some frustrations, a sound foundation has indeed been laid for future progress.

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Downward propagation of upper stratospheric mean zonal wind perturbation to the troposphere

Geophysical Research Letters ◽

10.1029/gl017i009p01263 ◽

1990 ◽

Vol 17 (9) ◽

pp. 1263-1266 ◽

Cited By ~ 109

Author(s):

Kunihiko Kodera ◽

Koji Yamazaki ◽

Masaru Chiba ◽

Kiyotaka Shibata

Keyword(s):

Zonal Wind ◽

Downward Propagation ◽

Wind Perturbation

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641 Aerodynamic characteristics of rotary wings at low Reynolds numbers

The proceedings of the JSME annual meeting ◽

10.1299/jsmemecjo.2006.5.0_203 ◽

2006 ◽

Vol 2006.5 (0) ◽

pp. 203-204

Author(s):

Takashi Ando ◽

Hikaru Aono ◽

Hao Liu

Keyword(s):

Reynolds Numbers ◽

Aerodynamic Characteristics ◽

Low Reynolds Numbers ◽

Low Reynolds ◽

Rotary Wings

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A Novel Design in Micro-Air-Vehicle: Flapping Rotary Wings

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.232.189 ◽

2012 ◽

Vol 232 ◽

pp. 189-193 ◽

Cited By ~ 9

Author(s):

Jiang Hao Wu ◽

Chao Zhou ◽

Yan Lai Zhang

Keyword(s):

Mechanical Model ◽

Lift Force ◽

Wing Length ◽

Angle Of Attack ◽

Micro Air Vehicle ◽

Air Vehicle ◽

Length And Area ◽

Rotary Wings ◽

Novel Design

A novel design in micro-air-vehicle using flapping rotary wings with different wing spanwise length and area is proposed. With the wings flapping, produced thrust makes the wings rotation. Furthermore, lift force from rotary wings increases and overcomes the MAV weight. On the basis of this principle, a mechanical model is made and sample experiments of averaged lift measurement in different wing length and area and angle of attack are executed. It is shown that the maximum averaged lift produced by micro flapping rotary wings can reach to 80mN approximately close to the weight of MAV.

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