A computational study of shock speeds in high-performance shock tubes

This paper describes U2DE, a finite-volume code that numerically solves the Euler equations. The code was used to perform multi-dimensional simulations of the gradual opening of a primary diaphragm in a shock tube. From the simulations, the speed of the developing shock wave was recorded and compared with other estimates. The ability of U2DE to compute shock speed was confirmed by comparing numerical results with the analytic solution for an ideal shock tube. For high initial pressure ratios across the diaphragm, previous experiments have shown that the measured shock speed can exceed the shock speed predicted by one-dimensional models. The shock speeds computed with the present multi-dimensional simulation were higher than those estimated by previous one-dimensional models and, thus, were closer to the experimental measurements. This indicates that multi-dimensional flow effects were partly responsible for the relatively high shock speeds measured in the experiments.

Test time in low pressure shock tubes.

"SSD-TDR-62-204. Report no TDR-169 (3230-12)TN-5."

Shock tube studies of the effects of sharp-rising, long-duration overpressures on biological systems /

Shock tubes have been used successfully by a number of investigators to study the biological effects of variations in environmental pressures (1,2,3). Recently an unusually versatile laboratory pressurization source became available with the capability of consistently reproducing a wide variety of pressure-time phenomena of durations equal to and well beyond those associated with the detonation of nuclear devices (4). Thus it became possible to supplement costly full-scale field research in blast biology carried out at the Nevada Test Site (5,6) by using an economical yet realistic laboratory tool. In one exploratory study employing pressure pulses of 5 to 10 sec duration wherein the times to max overpressure and the magnitudes of the overpressures were varied, a relatively high tolerance of biological media to pressures well over 150 psi was demonstrated (7). In contrast, the present paper will describe the relatively high biological susceptibility to long duration overpressures in which the pressure rises occurred in single and double fast-rising steps.

Interferometric measurement in a shock tube of dissociation rates for air and its component gases.

At head of title: Cornell University, Graduate School of Aeronautical Engineering.

Theory of electron driven shock waves

"STL/TR-60-0000-GR310."

Single-pulse shock tube studies of the kinetics of the reaction N + O [arrow right over arrow left (reversible reaction)] 2 NO between 2000-3000⁰ K,

At head of title: Combustion Dynamics Division, Air Force Office of Scientific Research, ARDC, Washington, D. C., File no. AF 18(600)-1332.

Plasma studies in a shock tube,

"This work was supported by the Air Research and Development Center, Griffis Air Force Base, New York."

Shock tube driver techniques and attenuation measurements,

"Contract AF 18(603)-10, Mechanics Division, Air Force Office of Scientific Research, ARDC, Washington."

Low-density research in the hypersonic shock tunnel

"The experimental study reported here has been performed under the sponsorship of the Fluid Dynamics Branch, Aeronautical Research laboratories of the U.S. Air Force Air Research and Development Command, Contract no. AF 33(616)-6025."

48-inch hypersonic shock tunnel; description and capabilities.

Mode of access: Internet.

Instrumentation for force and pressure measurements in a hypersonic shock tunnel

Mode of access: Internet.

Hypersonic research in the shock tunnel.

"Presented at the I.A.S. National Symposium on Hypervelocity Techniques, Denver, Colorado, October 20, 21, 1960."

Shock tunnel studies of high-enthalpy ionized airflows,

"AFOSR 3025."

Resistance thermometer for heat transfer measurement in a shock tube,

Army Ordinance contract no. DA-04-495-Ord-19.

Shock tube test time limitation due to turbulent wall boundary layer.

At head of title: SSD-TDR-63-78. Report no. TDR-169 (3230-12)TR-3.