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Title
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Investigation of Boundary-Layer Transition on Swept Wings at Mach Numbers 2.5 to 5
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Date
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1963
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Index Abstract
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Coming Soon
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Photo Quality
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Incomplete
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Report Number
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AEDC TDR 63-109
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Creator
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Pate, S. R.
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Brillhart, R. E.
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Corporate Author
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ARO, Inc.
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Extent
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41
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Identifier
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AD0410130
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Distribution Classification
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1
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Contract
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AF 40(600)-1000
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DoD Project
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1366
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DoD Task
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136612
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DTIC Record Exists
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Yes
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Distribution Change Authority Correspondence
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None
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Abstract
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Tests were conducted in the 12-in. Supersonic Tunnel of the von Karman Gas Dynamics Facility to determine boundary-layer transition locations on swept wings having a circular arc profile and modified arc profile. Test Mach numbers were from 2.5 to 5 over a Reynolds-number-per-inch range from 0.14 to 1. 08 million at sweep angles of 24, 36, and 50 deg for angles of attack of 0 and approximately -4 deg. Boundary-layer transition Reynolds numbers determined by a pitot probe, and results obtained visually with a sub limable solid are presented. The major factors influencing boundary-layer transition were wing sweep and model leading edge geometry. Increasing wing sweep and leading edge bluntness above a sweep angle of approximately 20 deg decreased the transition Reynolds number at all test Mach numbers.
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Report Availability
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Full text available by request
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Date Issued
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1963-07
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Publisher
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Arnold Air Force Station, TN : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force
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Provenance
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IIT
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Type
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report
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Format
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41 pages ; 28 cm.