An investigation into the characteristics of the wing tip vortex on
a flexible wing micro-air-vehicle (MAV) was conducted. The Air
Force Research Lab, Munitions Directorate designed a man-portable
MAV with a 24" wingspan and 6" root chord to be used for battle
damage assessment and reconnaissance or local surveillance. For
this MAV, two prototypes have been produced. One has a rigid wing
prepared from carbonfiber; the other has a flexible wing prepared
from parachute-latex material attached to a carbon-fiber frame. The
experiments were performed to investigate the wing displacement and
wing tip vortex interaction, characterizing the differences and
effects of wing displacement and the shifting and velocity of wing
tip vortex between two prototypes placed in typical operating
conditions. Initially, each aircraft model was mounted at the test
section in the low speed wind tunnel and exposed to various angles
of attack and wind conditions. An optical telescope was used to
measure the wing tip displacement and a tri-axial hot-wire
anemometer was used to capture the velocity profiles in the wind
tunnel to characterize wing tip vortex system. The results indicate
that the wing tip displacement of the flexible wing was
approximately 8 times than that of the rigid wing in an unstalled
condition. The data suggests that flexible wing has a denser
core-distribution of velocity within the wing tip vortex and delays
the angle at which separation occurs.
General
Imprint: |
Biblioscholar
|
Country of origin: |
United States |
Release date: |
October 2012 |
First published: |
October 2012 |
Authors: |
Hong Joon Park
|
Dimensions: |
246 x 189 x 5mm (L x W x T) |
Format: |
Paperback - Trade
|
Pages: |
92 |
ISBN-13: |
978-1-249-58644-9 |
Categories: |
Books >
Social sciences >
Education >
General
|
LSN: |
1-249-58644-5 |
Barcode: |
9781249586449 |
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