1887
banner image
No data available.
Please log in to see this content.
You have no subscription access to this content.
No metrics data to plot.
The attempt to load metrics for this article has failed.
The attempt to plot a graph for these metrics has failed.
Three-dimensional flow structure and aerodynamic loading on a revolving wing
Rent:
Rent this article for
USD
10.1063/1.4794753
/content/aip/journal/pof2/25/3/10.1063/1.4794753
http://aip.metastore.ingenta.com/content/aip/journal/pof2/25/3/10.1063/1.4794753

Figures

Image of FIG. 1.
FIG. 1.

Definition of the (a) wing geometry and (b) revolving configuration.

Image of FIG. 2.
FIG. 2.

Rotational angle in time.

Image of FIG. 3.
FIG. 3.

Near-field computational mesh.

Image of FIG. 4.
FIG. 4.

Effect of grid resolution on (a) the instantaneous flow structure and (b) the aerodynamic loads generated on the revolving wing for Re = 14 500 and θ = 30°.

Image of FIG. 5.
FIG. 5.

Instantaneous -criterion iso-surfaces ( = 5) showing the three-dimensional flow structure at various angles during the wing's rotation for 500 ⩽ Re ⩽ 60 000 and θ = 30°. For Re ⩾ 2 000, the time-averaged solution between ϕ = 90° and 270° is provided.

Image of FIG. 6.
FIG. 6.

Expanded view of the shear-layer substructure present for Re = 14 500 and ϕ = 90°.

Image of FIG. 7.
FIG. 7.

Instantaneous surface pressure (− ) contours on the suction side of the plate for 200 ⩽ Re ⩽ 60 000 and θ = 30°. For Re ⩾ 2000, the time-averaged solution between ϕ = 90° and 270° is provided.

Image of FIG. 8.
FIG. 8.

Iso-surfaces of relative total pressure ( / = 0.97 and 0.99) highlighting the vortex core after the unpinning and reconnection of the leading-edge and wing-tip vortices for each Reynolds number. Images correspond to a rotational angle of ϕ = 45°.

Image of FIG. 9.
FIG. 9.

Contours of relative span-wise velocity at 25%, 50%, and 75% span locations. A single contour line of relative total pressure ( / = 0.99) is superimposed in each image to highlight the leading-edge vortex. View is directed root-to-tip at ϕ = 90°.

Image of FIG. 10.
FIG. 10.

Span-wise locations of flow reversal within the leading-edge vortex core at a rotational angle of ϕ = 90°. Reversed flow was not encountered within the core for Re < 2000.

Image of FIG. 11.
FIG. 11.

Iso-surfaces of total pressure ( / = 0.96 and 0.99) highlighting the sudden expansion of the leading-edge vortex core for Re ⩾ 2000 at a rotational angle of ϕ = 90°.

Image of FIG. 12.
FIG. 12.

The instantaneous streamlines about the revolving wing for several rotational angles and Re = 500.

Image of FIG. 13.
FIG. 13.

Effect of Reynolds number on the (a) instantaneous aerodynamic loads, (b) mean forces, and (c) mean force ratio generated on the wing during its revolution at a fixed angle of θ = 30°. Mean lift and drag are taken between ϕ = 45° and 315°.

Image of FIG. 14.
FIG. 14.

Span-wise components of the centrifugal, Coriolis, pressure gradient, and total dynamic forces at 25%, 50%, and 75% span locations for Re = 2000 and ϕ = 90°. A single contour line of relative total pressure ( / = 0.99) is superimposed in each image to highlight the leading-edge vortex. View is directed root-to-tip at ϕ = 90°.

Image of FIG. 15.
FIG. 15.

Surface-normal components of the centrifugal, Coriolis, pressure gradient, and total dynamic forces at 25%, 50%, and 75% span locations for Re = 2000 and ϕ = 90°. A single contour line of relative total pressure ( / = 0.99) is superimposed in each image to highlight the leading-edge vortex. View is directed root-to-tip at ϕ = 90°.

Image of FIG. 16.
FIG. 16.

Contours of centrifugal, Coriolis, pressure gradient, and total dynamic force magnitudes at 25%, 50%, and 75% span locations for Re = 2000 and ϕ = 90°. A single contour line of relative total pressure ( / = 0.99) is superimposed in each image to highlight the leading-edge vortex. View is directed root-to-tip at ϕ = 90°.

Image of FIG. 17.
FIG. 17.

Net contribution of (a) the span-wise and (b) the surface-normal forces across the span. At each span-wise location, the forces are integrated across an area that extends from the wing surface to half a chord off the suction side and 0.1 off the leading- and trailing-edges.

Image of FIG. 18.
FIG. 18.

Instantaneous iso-surfaces of relative total pressure showing the vortex flow structure around the rotating and translating wings at . Corresponding images between the two cases match the stroke distance of the mid-span of the wing.

Image of FIG. 19.
FIG. 19.

Instantaneous surface pressure distribution for the rotating and translating wings at . Corresponding images between the two cases match the stroke distance of the mid-span of the wing.

Image of FIG. 20.
FIG. 20.

Instantaneous contours of relative span-wise velocity at 25%, 50%, and 75% span locations for the rotating and translating wings at at a mid-span stroke distance of ϕ = = 1.6.

Image of FIG. 21.
FIG. 21.

Aerodynamic loading for the rotating and translating wings at . Bottom image shows the corresponding mid-span stroke travel for both cases.

Image of FIG. 22.
FIG. 22.

Effect of geometric angle, θ, on the (a) instantaneous Q-criterion iso-surfaces ( = 5) and (b) surface pressure for Re = 500. Images correspond to a rotational angle of ϕ = 270°.

Image of FIG. 23.
FIG. 23.

Examination of (a) the mean forces, (b) the lift and drag polar, and (c) the lift-to-drag ratio with varying geometric angle relative to the rotational axis for Re = 500. Force values correspond to the average loads computed for 45° ⩽ ϕ ⩽ 315°.

Image of FIG. 24.
FIG. 24.

Mid-span, planar contours of instantaneous span-wise vorticity, ω, from the (a) computational solution and (b) experimental measurement at a rotational angle of ϕ = 90° and Reynolds number of 3600.

Image of FIG. 25.
FIG. 25.

Depiction of (a) the PIV-like sampling of the computational solution and the application of (b) non-overlapping and (c) overlapping local averaging.

Image of FIG. 26.
FIG. 26.

Mid-span, planar contours of span-wise vorticity for Re = 3600 and θ = 30°.

Tables

Generic image for table
Table I.

Baseline mesh dimensions.

Loading

Article metrics loading...

/content/aip/journal/pof2/25/3/10.1063/1.4794753
2013-03-15
2014-04-19
Loading

Full text loading...

This is a required field
Please enter a valid email address
752b84549af89a08dbdd7fdb8b9568b5 journal.articlezxybnytfddd
Scitation: Three-dimensional flow structure and aerodynamic loading on a revolving wing
http://aip.metastore.ingenta.com/content/aip/journal/pof2/25/3/10.1063/1.4794753
10.1063/1.4794753
SEARCH_EXPAND_ITEM