Flow characteristics of a 12-in. intermittent supersonic tunnel

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049 ‡aMAIN
086 0 ‡aD 301.45/33-2:63-203
100 1 ‡aAnderson, A., ‡eauthor.
245 1 0 ‡aFlow characteristics of a 12-in. intermittent supersonic tunnel / ‡cby A. Anderson.
264 1 ‡aArnold Air Force Station, Tennessee : ‡bArnold Engineering Development Center, Air Force Systems Command, United States Air Force, ‡c1963.
300 ‡a37 pages : ‡billustrations, ‡c28 cm
336 ‡atext ‡btxt ‡2rdacontent
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490 0 ‡aAEDC-TDR ; ‡v63-203
500 ‡a"September 1963."
504 ‡aIncludes bibliographic references (page 6).
520 ‡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).
536 ‡aReport prepared by ARO, Inc., under Air Force Contract No. ‡bAF 40(600)-1000.
538 ‡aMode of access: Internet.
650 0 ‡aBoundary layer.
650 0 ‡aSupersonic wind tunnels.
710 2 ‡aARO, Inc., ‡esponsor.
710 2 ‡aArnold Engineering Development Center, ‡esponsor.
710 1 ‡aUnited States. ‡bAir Force. ‡bSystems Command, ‡eissuing body.
730 0 ‡aTechnical Report Archive & Image Library (TRAIL)
899 ‡a39015104951358
CID ‡a102893245
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DAT 2 ‡a2024-07-29T17:30:02Z
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