Investigation of the Attenuation of Plane Shock Waves Moving over very Rough Surfaces

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Experimental measurements of the attenuation of plane shock waves moving over rough walls have been made in a shock tube. Measurements of the boundary-layer characteristics, including thickness and velocity distribution behind the shock, have also been made with the aid of new cal techniques which provide direct information on the local boundary-layer conditions at the rough walls. Measurements of shock speed and shock pressure ratio are presented for both smooth-wall and rough-wall flow over lengths of machined-smooth and rough strips which lined all four walls of the shock tube. A simplified theory based on Von Karman's expression for skin-friction coefficient ... continued below

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Huber, Paul W.; McFarland, Donald R. & Levine, Philip June 16, 1953.

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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 12 times . More information about this report can be viewed below.

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  • Main Title: Investigation of the Attenuation of Plane Shock Waves Moving over very Rough Surfaces
  • Series Title: NACA Research Memorandums

Description

Experimental measurements of the attenuation of plane shock waves moving over rough walls have been made in a shock tube. Measurements of the boundary-layer characteristics, including thickness and velocity distribution behind the shock, have also been made with the aid of new cal techniques which provide direct information on the local boundary-layer conditions at the rough walls. Measurements of shock speed and shock pressure ratio are presented for both smooth-wall and rough-wall flow over lengths of machined-smooth and rough strips which lined all four walls of the shock tube. A simplified theory based on Von Karman's expression for skin-friction coefficient for flow over rough walls, along with a wave-model concept and extensions to include time effects, is presented. In this theory, the shock-tube flow is assumed to be one-dimensional at all times and the wave-model concept is used to relate the local layer growth to decreases in shock strength. This concept assumes that local boundary-layer growths act as local mass-flow sinks, which give rise to expansion waves which, in turn, overtake the shock and lower its mass flow accordingly.

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  • URL: http://hdl.handle.net/2060/20050029466 External Link
  • Report No.: NACA-RM-SL53D13A
  • Center for AeroSpace Information Number: 20050029466
  • Archival Resource Key: ark:/67531/metadc64728

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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

  • June 16, 1953

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Oct. 19, 2017, 11:36 a.m.

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Huber, Paul W.; McFarland, Donald R. & Levine, Philip. Investigation of the Attenuation of Plane Shock Waves Moving over very Rough Surfaces, report, June 16, 1953; (digital.library.unt.edu/ark:/67531/metadc64728/: accessed July 21, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.