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220711s1963 tnua bt f000 0 eng d |
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‡a(MiU)99187625230806381
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‡aMAIN
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‡aD 301.45/33-2:63-203
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‡aAnderson, A.,
‡eauthor.
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‡aFlow characteristics of a 12-in. intermittent supersonic tunnel /
‡cby A. Anderson.
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‡aArnold Air Force Station, Tennessee :
‡bArnold Engineering Development Center, Air Force Systems Command, United States Air Force,
‡c1963.
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‡a37 pages :
‡billustrations,
‡c28 cm
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‡atext
‡btxt
‡2rdacontent
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‡aunmediated
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‡aAEDC-TDR ;
‡v63-203
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‡a"September 1963."
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‡aIncludes bibliographic references (page 6).
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‡aA compilation has been made of all calibration data obtained since 1958 in the von Karman Gas Dynamics Facility's 12-Inch Supersonic Tunnel (D). Test section flow characteristics are presented for the nominal Mach number range from 1.5 to 5 over the available Reynolds number range. Along the axis of the test section for all contours the maximum variation in Mach number is within =0.01, and the average flow angles in pitch and yaw are less than 0.2 deg. Somewhat larger variations in Mach number and flow angularity are found off-axis. At the higher Mach numbers, significant changes in the average test section Mach number with decreasing Reynolds number are accompanied by corresponding changes in the tunnel boundary layer. (Author).
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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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‡aBoundary layer.
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‡aSupersonic wind tunnels.
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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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‡aTechnical Report Archive & Image Library (TRAIL)
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