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Transonic nozzle flow of dense gases

Published online by Cambridge University Press:  26 April 2006

A. Kluwick
A. Kluwick
Affiliation:
Institut für Strömungslehre und Wärmeübertragung, Technische Universität Wien, A-1040 Wien, Austria
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Abstract

The paper deals with the flow properties of dense gases in the throat area of slender nozzles. Starting from the Navier–Stokes equations supplemented with realistic equations of state for gases which have relatively large specific heats a novel form of the viscous transonic small-perturbation equation is derived. Evaluation of the inviscid limit of this equation shows that three sonic points rather than a single sonic point may occur during isentropic expansion of such media, in contrast to the case of perfect gases. As a consequence, a shock-free transition from subsonic to supersonic speeds cannot, in general, be achieved by means of a conventional converging–diverging nozzle. Nozzles leading to shock-free flow fields must have an unusual shape consisting of two throats and an intervening antithroat. Additional new results include the computation of the internal thermoviscous structure of weak shock waves and a phenomenon referred to as impending shock splitting. Finally, the relevance of these results to the description of external transonic flows is discussed briefly.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 247 , February 1993 , pp. 661 - 688
Copyright
© 1993 Cambridge University Press

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