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Investigation of the Attenuation of Plane Shock Waves Moving over very Rough SurfacesExperimental 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.
Document ID
20050029466
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Huber, Paul W.
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
McFarland, Donald R.
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Levine, Philip
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
January 1, 1953
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-SL53D13A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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