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220711s1964 tnua bt f000 0 eng d |
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‡a(MiU)99187625224406381
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‡asdr-miu.99187625224406381
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‡a(OCoLC)1335037927
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‡aMAIN
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‡aD 301.45/33-2:64-014
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‡aPate, S. R.,
‡eauthor.
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‡aInvestigation of flow separation on a two-dimensional flat plate haveing a variable-san trailing-edge flap at M [free stream] = 3 and 5 /
‡cby S.R. Pate.
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‡aArnold Air Force Station, Tennessee :
‡bArnold Engineering Development Center, Air Force Systems Command, United States Air Force,
‡c1964.
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‡a43 pages :
‡billustrations,
‡c28 cm
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‡atext
‡btxt
‡2rdacontent
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‡aunmediated
‡bn
‡2rdamedia
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‡avolume
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‡aAEDC-TDR ;
‡v64-014
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‡a"March 1964."
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‡aIncludes bibliographic references (pages 12-13).
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‡aAn experimental investigation of separated boundary-layer flow was conducted on a two-dimensional flat plate having a variable-span trailing edge flap in the 12-in. Supersonic Tunnel (D) of the von Karman Gas Dynamics Facility. The tests were made at Mach numers 3 and 5 at zero angle of attack and over a Reynolds number range (based on plate length) from 0.26 to 16.7 x 10 to the 6th power. Model surface pressure distributions, schlieren photographs, and velocity distributions are presented. The effects of unit Reynolds number, plate length, flap span, and flap deflection angle on the separated region are investigated, and comparisons are made with existing theory.
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536 |
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‡aReport prepared by ARO, Inc., under Air Force Contract No.
‡bAF 40(600)-1000.
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‡aMode of access: Internet.
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‡aLaminar boundary layer.
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‡aTrailing edges (Aerodynamics)
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‡aTrailing edge flaps.
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‡aARO, Inc.,
‡esponsor.
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‡aArnold Engineering Development Center,
‡esponsor.
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‡aUnited States.
‡bAir Force.
‡bSystems Command,
‡eissuing body.
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730 |
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‡aTechnical Report Archive & Image Library (TRAIL)
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‡a39015104951473
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