The Problem of Pneumatic Pressure Lag: Part 2—Unsteady Flow in a Tubing System Closed at One End

[+] Author and Article Information
A. L. Ducoffe, F. M. White

Georgia Institute of Technology, Atlanta, Ga.

J. Basic Eng 86(2), 241-246 (Jun 01, 1964) (6 pages) doi:10.1115/1.3653046 History: Received August 22, 1962; Online November 03, 2011


The results of the steady-state analysis presented in Part 1 are applied to a quasi-steady analysis isothermal flow in constant diameter tubes (with straight-through unions at the extremities) connected to a closed sensing volume. The ranges of transient pressure inputs and geometric variables were chosen to simulate typical missile pressure sensing systems. The effect of high inlet temperature during descent was not studied, all tests being at room temperature. The correlation of theory with experiment for three types of input (impulse, continuous, and shock) is shown to be quantitative over the range of variables studied. It is concluded that the empirical analysis presented herein provides an adequate working theory for pressure lag during transient flight.

Copyright © 1964 by ASME
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