A low-speed wind tunnel study and flight tests were performed to
examine the effects of a wing fence on the T-38A. Wind tunnel
results were based upon force and moment data collected with a
six-component balance and flow visualization at Reynolds numbers up
to 0.3 x 106, based on mean aerodynamic chord. The model did not
include the last 7.79 feet of the aircraft, and the engine and
exhaust were modeled as through-holes. Five fence geometries,
placed at wing station 125 ( 0.825 semispan), were compared. The
best performer of these designs, based on drag polar, was the fence
that wrapped the leading edge and extended 84.6 percent of the
local chord length along the wing's upper surface. Wind tunnel data
showed that this fence increased the lift coefficient by up to 6.3
0.6 percent and reduced spanwise and separated flow outboard the
fence. The flight-tested fence was based on the best performing
fence design from the wind tunnel study. The results were based on
aircraft instrumentation and flow visualization at Reynolds numbers
up to 9.98 x 106. It was inconclusive whether the fence caused an
increase in lift coefficient. The fence reduced the roll-off
tendency and wing rock during approaches to stall. Tuft
visualization on the aircraft wing suggested that the fence reduced
spanwise and separated flow outboard the fence, which agreed with
the wind tunnel results.
General
Imprint: |
Biblioscholar
|
Country of origin: |
United States |
Release date: |
September 2012 |
First published: |
September 2012 |
Authors: |
Michael D. Williams
|
Dimensions: |
246 x 189 x 14mm (L x W x T) |
Format: |
Paperback - Trade
|
Pages: |
270 |
ISBN-13: |
978-1-249-45664-3 |
Categories: |
Books >
Social sciences >
Education >
General
|
LSN: |
1-249-45664-9 |
Barcode: |
9781249456643 |
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