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Title
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Investigation of Boundary-Layer Suction on a 20-Caliber Orgive Cylinder at Mach Numbers 2.5, 3.0, 3.5, and 4.0
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Date
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1961
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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 TN 61-66
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Creator
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Strike, W. T.
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Pate, S.
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Corporate Author
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VKF, ARO, Inc.
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Extent
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30
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Identifier
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AD0257381
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Distribution Classification
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1
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Contract
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AF 40(600)-800
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DoD Project
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1366
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DoD Task
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14080
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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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A second investigation was conducted in the 12in., intermittent, supersonic wind tunnel of the von Karman Gas Dynamics Facility to measure the effectiveness of boundary-layer suction on a 20 caliber ogive cylinder. The application of suction type boundary-layer control on the ogive was investigated at Mach numbers 2.5, 3.0, 3.5, and 4.0 over a unit Reynolds number range from 0. 07 to 1.03 x 10 to the 6th power per inch with the model at zero angle of attack. Some additional data were obtained at 2-deg angle of attack at Mach number 3. As a result of improving the design of the suction system a significant gain was made in reducing the net drag of the model at Mach number 3 by boundary-layer suction. The presence of the suction slots with no suction when compared with the sealed slot configuration (that is, smooth model) had some influence on the boundary-layer characteristics at all 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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1961-06
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Publisher
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Arnold Air Force Station, TN : Arnold Engineering Development Center, Air Force Systems Command, USAF
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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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30 pages ; 28 cm.