Turbulent boundary-layer and skin-friction measurements in axial flow along cylinders at Mach numbers between 0.5 and 3.6

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Description

Report presenting experiments that have been conducted to determine average skin-friction coefficients in the absence of heat transfer for completely turbulent flow along the cylindrical portion of cone-cylinder bodies of revolution with several overall fineness ratios. Numerous boundary-layer surveys were made to enable all data to be based on an effective starting position of the turbulent flow. Results regarding tripping devices to insure turbulent flow, effect of nose shape, attainment of equilibrium in the blowdown tunnel, a comparison of data from wind tunnels, effect of pressure gradient, and skin friction values using several different configurations are provided.

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53 p. : ill.

Creation Information

Chapman, Dean R. & Kester, Robert H. March 1954.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 303 times . More information about this report can be viewed below.

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  • Main Title: Turbulent boundary-layer and skin-friction measurements in axial flow along cylinders at Mach numbers between 0.5 and 3.6
  • Series Title: NACA Technical Notes

Description

Report presenting experiments that have been conducted to determine average skin-friction coefficients in the absence of heat transfer for completely turbulent flow along the cylindrical portion of cone-cylinder bodies of revolution with several overall fineness ratios. Numerous boundary-layer surveys were made to enable all data to be based on an effective starting position of the turbulent flow. Results regarding tripping devices to insure turbulent flow, effect of nose shape, attainment of equilibrium in the blowdown tunnel, a comparison of data from wind tunnels, effect of pressure gradient, and skin friction values using several different configurations are provided.

Physical Description

53 p. : ill.

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  • Accession or Local Control No: 93R13091
  • URL: http://hdl.handle.net/2060/19930083801 External Link
  • Report No.: NACA-TN-3097
  • Center for AeroSpace Information Number: 19930083801
  • Archival Resource Key: ark:/67531/metadc56932

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

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Creation Date

  • March 1954

Added to The UNT Digital Library

  • Nov. 16, 2011, 7:33 a.m.

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  • April 6, 2018, 2:29 p.m.

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Chapman, Dean R. & Kester, Robert H. Turbulent boundary-layer and skin-friction measurements in axial flow along cylinders at Mach numbers between 0.5 and 3.6, report, March 1954; (digital.library.unt.edu/ark:/67531/metadc56932/: accessed June 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.