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naca-rm-a9k02

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National Advisory Committee for Aeronautics, Research Memorandum - Investigation of Downwash and Wake Characteristics at a Mach Number of 1.53 - III - Swept Wings

The results of an emerimental investigation of the downwash and
wake characteristics behind two highly swept wings in a supersonic stream
are presented. {the leadinghedge sweep angles of the two wings were 630
and 63011-5', the aspect ratios were 3. 50 and 1.66, and the corresponding
taper ratios were 0 .25 and 1.00. ‘flle Mach number of the tests was 1.53
and the Reynolds nmnbers based. on the mean aerodynamic chords ware 1.1!-
million for the tapered. wing and 2. 6 million for the untapered wing.
Measurements Were made of the variation of downwash angle with angle of
attack at several positions within the induced flow field. Additional
surveys were made to determine the position and extent of the friction
wake. The experimental downwash results were compared with the charac—
teristics calculated. by means of the linear theory.

Agreement between the experimental and theoretical values of the
rate of change of downwash angle with angle of attack at zero lift was
good only at isolated points. In general, the experimental values for
the tapered wing were much less than the theoretical. At most of the
survey points the rate of change of downwash angle with angle of attack
for the tapered wing did not exceed, at any angle of attack, the cor—
responding theoretical values of the rate of change of downwash at zero
lift. The differences between the experimental results for the untapered
wing and the theoretical calculations are believed to result from dif—
ferences between the actual load distribution and that calculated by
theory.

The general characteristics of the friction wake were similar to
those observed in subsonic flow. With increasing distance downstream
from the trailing edge the wake expanded and, with the wing at positive
angles of attack, moved downward relative to the free—stream direction.
In general, the maximum pitot—pressure loss at the wake center line
decreased with increasing distance behind the trailing edge.

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naca-rm-a9k02

  • Version
  • 0 Downloads
  • 1.35 MB File Size
  • 1 File Count
  • April 20, 2017 Create Date
  • April 20, 2017 Last Updated
Scroll for Details

National Advisory Committee for Aeronautics, Research Memorandum - Investigation of Downwash and Wake Characteristics at a Mach Number of 1.53 - III - Swept Wings

The results of an emerimental investigation of the downwash and
wake characteristics behind two highly swept wings in a supersonic stream
are presented. {the leadinghedge sweep angles of the two wings were 630
and 63011-5', the aspect ratios were 3. 50 and 1.66, and the corresponding
taper ratios were 0 .25 and 1.00. ‘flle Mach number of the tests was 1.53
and the Reynolds nmnbers based. on the mean aerodynamic chords ware 1.1!-
million for the tapered. wing and 2. 6 million for the untapered wing.
Measurements Were made of the variation of downwash angle with angle of
attack at several positions within the induced flow field. Additional
surveys were made to determine the position and extent of the friction
wake. The experimental downwash results were compared with the charac—
teristics calculated. by means of the linear theory.

Agreement between the experimental and theoretical values of the
rate of change of downwash angle with angle of attack at zero lift was
good only at isolated points. In general, the experimental values for
the tapered wing were much less than the theoretical. At most of the
survey points the rate of change of downwash angle with angle of attack
for the tapered wing did not exceed, at any angle of attack, the cor—
responding theoretical values of the rate of change of downwash at zero
lift. The differences between the experimental results for the untapered
wing and the theoretical calculations are believed to result from dif—
ferences between the actual load distribution and that calculated by
theory.

The general characteristics of the friction wake were similar to
those observed in subsonic flow. With increasing distance downstream
from the trailing edge the wake expanded and, with the wing at positive
angles of attack, moved downward relative to the free—stream direction.
In general, the maximum pitot—pressure loss at the wake center line
decreased with increasing distance behind the trailing edge.

FileAction
naca-rm-a9k02 Investigation of Downwash and Wake Characteristics at a Mach Number of 1.53 - III - Swept Wings.pdfDownload 
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967656 Total Downloads

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Newest Additions

AA-SM-026-122
AA-SM-026-122 Beam Analysis – Compression Flexure – Fixed One End, ...
AA-SM-026-121
AA-SM-026-121 Beam Analysis – Compression Flexure – Fixed One End, ...
AA-SM-026-120
AA-SM-026-120 Beam Analysis – Compression Flexure – Fixed Both Ends, ...
AA-SM-026-119
AA-SM-026-119 Beam Analysis – Compression Flexure – Fixed Both Ends, ...
AA-SM-026-118
AA-SM-026-118 Beam Analysis – Compression Flexure – Simply Supported and ...