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...

Full description

Saved in:
Bibliographic Details
Main Author: Mirels, Harold
Corporate Author: United States. National Advisory Committee for Aeronautics
Format: Government Document Book
Language:English
Published: Washington, D.C. : National Advisory Committee for Aeronautics, 1954.
Series:Technical note (United States. National Advisory Committee for Aeronautics) ; 3278.
Subjects:

PASCAL Offsite

Holdings details from PASCAL Offsite
Call Number: Y 3.N 21/5:6/3278
Y 3.N 21/5:6/3278 Available Place a Hold