2 edition of Laser-velocimeter surveys of merging vortices in a wind tunnel found in the catalog.
Laser-velocimeter surveys of merging vortices in a wind tunnel
Victor R Corsiglia
by National Aeronautics and Space Administration, Scientific and Technical Information Office, for sale by the National Technical Information Service in [Washington], Springfield, Va
Written in English
|Statement||Victor R. Corsiglia, Ames Research Center, James D. Iversen, Iowa State University, Kenneth L. Orloff, Ames Research Center|
|Series||NASA technical memorandum ; 78449|
|Contributions||Iversen, James D., joint author, Orloff, Kenneth L., joint author, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Ames Research Center, Iowa State University|
|The Physical Object|
|Pagination||iii, 44 p. :|
|Number of Pages||44|
The also claimed that increasing the amplitude and frequency of pulsation intensifies the rate of transport phenomena. By decreasing the frequency, vortices that develop in the shearing layer merge with each other near the stagnation region. Vortex merging is observed at the frequencies of and 3 Hz but not for 6 and 9 Hz. For a basic ground vehicle type of bluff body, the time averaged wake structure is analysed. At a model length based reynolds number of million, detailed pressure measurements, wake survey and force measurements were done in a wind tunnel. Some flow visualisation results were also obtained. Geometric parameter varied was base slant angle.
Fig. 10 shows two examples of such flows ob- tained in a water tunnel facility . Interactions of multiple vortices, complex vortex patterns, coiling-up and merging, vortex breakdown, and unsteady interactions are highly chal- lenging vortical flows. These aspects are even more complex and challenging for manoeuvring aircraft. Recent wind tunnel tests (refs. 1 to 3) have provided data on the three advanced high-speed propeller models described in table I. The SR-7A model is the most recent in a series of single-rotation designs (ref. h) and is an aero- elastically scaled model of the 9-f t-diameter Large-Scale Advanced Propeller (LAP) being used in the Propfan Test.
For a basic ground vehicle type of bluff body, the time averaged wake structure is analysed. At a model length based Reynolds number of million, detailed pressure measurements, wake survey and force measurements were done in a wind tunnel. Some flow visualisation results were also obtained. Geo. In the wind tunnel experiment, two normal hot-wire probes were situated at the outer edges of the wake shear layers originated from the two normal plates for measuring the vortex-shedding frequencies. Figure 3(a) shows the vortex-shedding frequencies in the non-dimensional form, i.e. Strouhal numbers of fl) /U,, measured in (a) Figure 2.
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Laser-Velocimeter Surveys of Merging Vortices in a Wind Tunnel Article (PDF Available) in Journal of Aircraft 15(11) February with 43 Reads How we measure 'reads'. Laser-velocimeter surveys of merging vortices in a wind tunnel. [Washington]: National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va.: For sale by the National Technical Information Service, American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by: Laser-velocimeter surveys of merging vortices in a wind tunnel.
By V. Corsiglia, K. Orloff and J. Iversen. Abstract. The merger of two vortices was studied with a laser velocimeter designed to measure the two cross-stream components of velocity.
Measurements were made at several downstream distances in the vortex wake shed by two. Laser-velocimeter surveys of merging vortices in a wind tunnel: Complete data and analysis. By V. Corsiglia, K. Orloff and J. Iversen. Abstract. The merger of two corotating vortices was studied with a laser velocimeter designed to measure the two cross-stream components of velocity.
Measurements were made at several downstream. Laser-velocimeter surveys of merging vortices in a wind tunnel: complete data and analysis / By Victor R. Corsiglia, joint author. Kenneth L.
Orloff, joint author. T.J. Craft, B.E. Launder, C.M.E. Robinson. The Computational Modelling of Wing-Tip Vortices and their Near-Field Decay.
Engineering Turbulence Modelling and. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Books.
AIAA Education Series; Library of Flight; Reynolds number dependence of two-dimensional laminar co-rotating vortex merging. 1 March | Theoretical and Computational Fluid Dynamics, Vol.
19, No. Laser-Velocimeter Surveys of Merging Vortices in a Wind Tunnel. laser-velocimeter surveys of merging vortices in a wind tunnel introduced by excursions of the central vortex filament within a wind tunnel test basic concepts of operation of the.
Single and multiple trailing vortices shed from semispan wings and a transport model in a wind tunnel were studied by means of a laser velocimeter, hot-wire anemometer, and trailing model. ABSTRACTA new wind tunnel has been constructed to study the mass transport properties of wind-blown sand.
This report on the first set of experiments in the new wind tunnel concerns the effect of. Wind Tunnel Unsteady Flow Corsiglia, V.R., Iversen, J.D.
and Orloff, K.L., Laser-velocimeter surveys of merging vortices in a wind tunnel. AIAA 16th Aerospace Sciences Meeting, Huntsville, Alabama Google Scholar. Buy this book on publisher's site; Reprints and Permissions; Personalised recommendations. Abstract. A helicopter rotor wake is dominated by strong vortices that form at each blade tip, e.g.
Refs. –. When the helicopter is descending or maneuvering, the blades may closely intersect the tip vortices resulting in a phenomenon known as blade vortex interaction (BVI).
Corsiglia, V. R.; Iversen, J. D.; Orloff, K. Laser velocimeter surveys of merging vortices in a wind tunnel. Aircr. 15, – Engel, M. A wind-tunnel investigation of a wing-tip trailing vortex.
1 thesis, AOE Dept, VPI, Blacksburg, VA. Francis, T. & Katz, J. Observations on the development of a tip vortex on a rectangular hydrofoil. Performance of a vortex-shedding anemometer is evaluated over the speed range of feet per minute to feet per minute.
Tests on two units were performed in the NBS Low Velocity Airflow Facility which provides a uniform flow of low turbulence and utilizes a laser velocimeter as the velocity standard. In-flight and wind tunnel leading edge vortex study on the FB airplane, NASA-CP, pp –, V.J. Convective merging of vortex cores in lift-generated wakes, AIAA K.L.
Laser-Volocimeter Surveys of Merging Vortices in a Wind Tunnel-Complete Data and Analysis, NASA-TM, October Smits, A.J. and Kummer, R.P. Recently a test was conducted in the NASA Lewis 9' X 15' Wind Tunnel of a forward—swept rotor which had 30 degrees of leading edge sweep over the outer 40% of the blade span.
The initial purpose. Zhang et al. () performed a wind tunnel experiment to study tip-vortex structures behind a standalone wind turbine model using PIV and hot-wire anemometry (HWA).
The 2D vorticity as well as swirling strength contours calculated from PIV measurements revealed stronger tip-vortex signatures near the top tip compared to those at the bottom tip. Experimental evidence is reported, regarding the formation of a pair of co-rotating tip vortices by a split wing configuration, consisting of two half wings at equal and opposite angles of attack.
Simultaneous measurements of the three-dimensional vector fields of velocity and vorticity were conducted on a cross plane at a downstream distance corresponding to cord lengths (near wake.JOURNAL ARTICLES, MEETING PAPERS, BOOKS AND CHAPTERS OF BOOKS. 5. Jones, R. T. The Oblique Wing - Aircraft Design for Transonic and Low Supersonic Laser Velocimeter Measurements of Two-Bladed Helicopter Rotor Flow Fields.
NASA TM X N Laser-Velocimeter Surveys of Merging Vortices in a Wind Tunnel. N Davis.For the moderately stable regime, a similar vortex merging process occurs for vortex number n = 8 & 9, resulting in the vortex merging between n = 10 & 11 and 12 & Figure Spanwise slice of isocontours of the vorticity field of the upper tip-vortex has been isolated for WT in (a) low-stable; (b) moderately-stable ABL regime.