Compressible Flow in a Long Tube Closed at One End
Abstract
Attention is given to pressure variations in a line that terminates at a sensing instrument of negligible volume, constituting a long tube that is closed at one end. An elementary derivation of the response equation that evolves from the laminar flow of a gas moving at subsonic speed is obtained, together with a closed form solution for the limiting case of slowly varying pressure gradients. After the transient phase, the difference in pressures acting at the ends of the duct is proportional to the coefficient of fluid viscosity, the square of the tube length/diameter ratio, and the time rate of change of the applied pressure; it is also inversely proportional to the magnitude of the pressure.
 Publication:

Journal of Spacecraft and Rockets
 Pub Date:
 November 1985
 DOI:
 10.2514/3.25787
 Bibcode:
 1985JSpRo..22..661B
 Keywords:

 Compressible Flow;
 Gas Flow;
 Missiles;
 Pipe Flow;
 Laminar Flow;
 Pressure Distribution;
 Subsonic Flow;
 Fluid Mechanics and Heat Transfer