The vortex kinematics associated with an oscillating delta wing

Huyer, Stephen A.; Luttges, Marvin W.

doi:10.2514/6.1991-1797

Cited by 4 publications

(8 citation statements)

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“…A great deal of information regarding unsteady aerodynamics has been gained through research at the University of Colorado [13][14][15][16][17][18][19]. Wind tunnel tests have been conducted for pitching and oscillating wings in constant fre estream velocity.…”

Section: Discussionmentioning

confidence: 99%

“…This seems reasonable, because the flow would be characterized by deep stall and the boundary layer would be separated throughout the rotation cycle. Reatt achment of the boundary layer has also been shown to be a necessary condition for the generation of a cohesive vortex structure [13][14][15][16][17][18][19]. AOA variations in the post-stall regime, however, did result in weak, diffuse vortex formations, and additional lift compared with static values was observed.…”

Section: Tower Wake Effectsmentioning

confidence: 99%

“…The formation of discrete, cohesive vortex structures may be considered part of the unsteady separated flow development process. The formation of dynamic stall vortices has been seen in wind tunnel tests for pitching or oscillating airfoils [10][11][12][13][14][15][16][17][18][19]. Although the blades on this particular wind turbine do not pitch or oscillate, yawing of the rotor disk with respect to the wind, sudden wind gusts, or passage through the wake of a cylindrical tower may produce geometrically similar effects.…”

Section: Introductionmentioning

confidence: 99%

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Examination of forced unsteady separated flow fields on a rotating wind turbine blade

Huyer

1993

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Price: Microfiche A01 Printed Copy A 11 Codes are used for pricing all publications. The code is determined by the number of pages in the publication. Information pertaining to the pricing codes can be found in the current issue of the following publications which are generally available in most libraries: Energy Research Abstracts (ERA); Government Reports Announcements and Index (GRA and/); Scientific

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Section: Discussionmentioning

confidence: 99%

Section: Tower Wake Effectsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Examination of forced unsteady separated flow fields on a rotating wind turbine blade

Huyer

1993

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“…The formation of discrete, cohesive vortex structures may be considered part of the unsteady -__ separated flow development process. The formation of dynamic stall vortices has been seen in wind _ tunnel tests fbr pitching or oscillating airfoils [10][11][12][13][14][15][16][17][18][19]. Although the blades on this particular wind turbine do not pitch or oscillate, yawing of the rotor disk with respect to the wind, sudden wind gusts, or passage through the wake of a cylindrical tower may produce geometrically similar effects.…”

Section: Introductionmentioning

confidence: 99%

Examination of forced unsteady separated flow fields on a rotating wind turbine blade

Huyer¹

1993

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Thisreportwas preparedas an accountof worksponsoredbyan agencyofthe UnitedStatesgovemment. Neitherthe UnitedStates govemrnent norany agency thereof, norany of their employees,make,_any warranty, expressor implied,or assumesany legalliabilityor responsibility forthe accuracy, completeness, or usefulnessofany information, apparatus,product, or processdisdosed, orrepresentsthat itsuse wouldnot infringeprivatelyownedrights. Reference herein to any specificcommercial product,process, or service by trade name, trademark, manufacturer,or otherwisedoes not necessarily constituteor implyitsendorsement, recommendation, or favoringbythe UnitedStatasgovernmentor anyagencythereof. The viewsand opinionsof authors expressedhereindo not necessarilystate or reflectthoseof the UnitedStates governmentor anyagency thereof.

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“…Much of the work done so far is limited to two-dimensional rectangular wings, and restricted to events occurring in the midspan plane of the airfoil (see Ahmed et al 1991, 1991, 1991, Huyer et al 1991, Kim et al 1991, Liou et al 1990, Ohmi et al 1990, and Park et al 1990 ). There is very little comparable work performed on threedimensional unsteady vortex dynamics in the near wake of the wing.…”

Section: Previous Studies Of the Wing-tip Vortexmentioning

confidence: 99%

An Experimental Study of Wing Tip Vortex in the Near Wake of a Rectangular Wing

Zheng¹,

Ramaprian²

1993

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9407 0OZ4; BestAvailable Copy REPORT DOCUMENTATION PAGE orme ApNov07e18Put~ mcor?.nq ow'Qen -of this collemtOn of ntohmat-om -% estimated to *,eage I out oer opiforse. ricludingq Ithe . tiowo reviewing instructions. s.arcninq; e.,%t~n data tOcM( 4a6ttcrmiq ard maintaining It.t daia neogeded and connaeelinq and re,ev.cmnq the ýotiemtoni of information Send commentsrqr~t nbsaneI~co n tt.i~tO ~.(o11"t.on at ntormnat,on. .ncic.Jang %.gt~ton*l ?or reduci.ng It"ý urdeft to VVh~nqton raicaduarteri, Service% jS . . SUPPLEMENTARY NOTESThe view, opinions and/or findings contained in this report are those of the author(s) and should not be construed as an official Department of the Army position, policy, or decision, unless so designated by oth.L: documentation. Approved for public release; distribution unlimited. ABSTRACT (Maximum 200 words)An experimental study of the tip-vortex behind a NACA 0015 rectangular wing of aspect ratio 4 was carried out to understand the structure and evolution of the vortex in the near-wake region.The results of these experimental studies are presented in this report. These measurements were made nonintrusively using three-component laser-Doppler veloicimetry (LDV). The experiments were carried out at a Reynolds number of about 180,000 in a low-speed wind tunnel. Two cases were studied, namely, (i) stationary wing and (ii) wing oscillating in pitch sinusoidally about its quarter-chord axis. The flow properties measured were the three components of the instantaneous velocity. These data were processed to obtain time-mean and phase-locked flow properties such as velocity, vorticity and turbulence. The data were obtained at several locations at 0.15 -3.0 chord lengths downstream from the trailing edge. The typical distributions of mean velocity, vorticity, circulation and turbulent intensity in the near wake are presented and discussed for the stationary wing. In the case of the oscillating wing, the phase-locked velocity, vorticity and turbulence data show details of the evolution of the unsteady tip vortex downstream from the trailing edge. The results also show that the flow is strongly non-quasi-steady at the oscillation frequency studied. The results are fully archived on tape and are available to any interested reader. These can be used as database in the development of wake models for the finite wing, and in studies of 296-102 GENERAL INSTRUCTIONS FOR COMPLETING SF 26The Report Documentation Page (RDP) is used in announcing and cataloging reports. It is important that this information be consistent with the rest of the report, particularly the cover and title page. ABSTRACTAn experimental study of the tip vortex behind a NACA 0015 rectangular wing of aspect ratio 4 was carried out to understand the structure and evolution of the vortex in the near-wake region. The results of these experimental studies are presented in this report. These measurements were made nonintrusively using three-component laserDoppler velocimetry (LDV). The experiments were carried out at a Reynolds number of ab...

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The vortex kinematics associated with an oscillating delta wing

Cited by 4 publications

References 4 publications

Examination of forced unsteady separated flow fields on a rotating wind turbine blade

Examination of forced unsteady separated flow fields on a rotating wind turbine blade

Examination of forced unsteady separated flow fields on a rotating wind turbine blade

An Experimental Study of Wing Tip Vortex in the Near Wake of a Rectangular Wing

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