Attenuation in a shock tube due to unsteady-boundary-layer action / Harold Mirels.
A method is presented for obtaining the attenuation of a shock wave in a shock tube due to the unsteady boundary layer along the shock-tube walls. It is assumed that the boundary layer is thin relative to the tube diameter and induces one-dimensional longitudinal pressure waves whose strength is pro...
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Corporate Author: | |
Format: | Government Document Book |
Language: | English |
Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1954.
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Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
3278. |
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Call Number: |
Y 3.N 21/5:6/3278
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Y 3.N 21/5:6/3278 | Available Place a Hold |