A Theory for Predicting the Flow of Real Gases in Shock Tubes with Experimental Verification
A Theory for Predicting the Flow of Real Gases in Shock Tubes with Experimental Verification

Author: Robert L. Trimpi

Publisher:

Published: 1955

Total Pages: 674

ISBN-13:

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The nonlinear characteristic differential equations applicable to a quasi-one-dimensional unsteady channel flow with friction and heat transfer are linearized and integrated in functional form for the particular study of small perturbations from ideal shock-tube flows. If the equivalence of unsteady- and steady-flow boundary layers is assumed, the problem of determining the perturbation in the unsteady flow reduces to an evaluation of the drag of a flat plate in the equivalent steady flow.

Shock Tubes
Shock Tubes

Author: Irving Israel Glass

Publisher: University of Toronto Press

Published: 1970-12-15

Total Pages: 852

ISBN-13: 1487597584

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This volume contains the proceedings of a symposium held at the University of Toronto in June 1969. The symposium consisted of six sessions; each containing an invited paper, followed by six contributed papers reporting on recent, relevant research and development. The topics are: a review of research problems in basic shock tube flows and the possibilities for the shock tube in the future; driving techniques; explosive drivers; theoretical and experimental research in electromagnetic shock tubes; chemical kinetics and spectroscopy; and a review of shock tube diagnostics, instrumentation and fundamental data as well as the measurement of physical quantities.

A Nonlinear Theory for Predicting the Effects of Unsteady Laminar, Turbulent, Or Transitional Boundary Layers on the Attenuation of Shock Waves in a Shock Tube with Experimental Comparison
A Nonlinear Theory for Predicting the Effects of Unsteady Laminar, Turbulent, Or Transitional Boundary Layers on the Attenuation of Shock Waves in a Shock Tube with Experimental Comparison

Author: Robert L. Trimpi

Publisher:

Published: 1958

Total Pages: 682

ISBN-13:

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The linearized attenuation theory of NACA Technical Note 3375 is modified in the following manner: (a) an unsteady compressible local skin-friction coefficient is employed rather than the equivalent steady-flow incompressible coefficient; (b) a nonlinear approach is used to permit application of the theory to large attenuations; and (c) transition effects are considered. Curves are presented for predicting attenuation for shock pressure ratios up to 20 and a range of shock-tube Reynolds numbers. Comparison of theory and experimental data for shock wave strengths between 1.5 and 10 over a wide range of Reynolds numbers shows good agreement with the nonlinear theory evaluated for a transition Reynolds nuniber of 2.5 million.