Investigation of conjugate circular arcs in rocket nozzle contour design

Investigation of conjugate circular arcs in rocket nozzle contour design The use of conjugate circular arcs in rocket nozzle contour design has been investigated by numerically comparing three existing sub-scale nozzles to a range of equivalent arc-based contour designs. Three performance measures were considered when comparing nozzle designs: thrust coefficient, nozzle exit wall pressure, and a transition between flow separation regimes during the engine start-up phase. In each case, an equivalent arc-based contour produced an increase in the thrust coefficient and exit wall pressure of up to 0.4 and 40% respectively, in addition to suppressing the transition between a free and restricted shock separation regime. A general approach to arc-based nozzle contour design has also been presented to outline a rapid and repeatable process for generating sub-scale arc-based contours with an exit Mach number of 3.8–5.4 and a length between 60 and 100% of a 15 conical nozzle. The findings suggest that conjugate circular arcs may represent a viable approach for producing sub-scale rocket nozzle contours, and that a further investigation is warranted between arc-based and existing full-scale rocket nozzles. Keywords Rocket nozzle · Supersonic flow · Contour design 1 Introduction 1. Sufficient thrust coefficient. 2. Ensure full-flowing engine operation at low altitude (suf- The increasing use of satellite http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Shock Waves Springer Journals

Investigation of conjugate circular arcs in rocket nozzle contour design

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Publisher
Springer Berlin Heidelberg
Copyright
Copyright © 2018 by Springer-Verlag GmbH Germany, part of Springer Nature
Subject
Engineering; Engineering Thermodynamics, Heat and Mass Transfer; Fluid- and Aerodynamics; Engineering Fluid Dynamics; Thermodynamics; Acoustics; Condensed Matter Physics
ISSN
0938-1287
eISSN
1432-2153
D.O.I.
10.1007/s00193-018-0834-0
Publisher site
See Article on Publisher Site

Abstract

The use of conjugate circular arcs in rocket nozzle contour design has been investigated by numerically comparing three existing sub-scale nozzles to a range of equivalent arc-based contour designs. Three performance measures were considered when comparing nozzle designs: thrust coefficient, nozzle exit wall pressure, and a transition between flow separation regimes during the engine start-up phase. In each case, an equivalent arc-based contour produced an increase in the thrust coefficient and exit wall pressure of up to 0.4 and 40% respectively, in addition to suppressing the transition between a free and restricted shock separation regime. A general approach to arc-based nozzle contour design has also been presented to outline a rapid and repeatable process for generating sub-scale arc-based contours with an exit Mach number of 3.8–5.4 and a length between 60 and 100% of a 15 conical nozzle. The findings suggest that conjugate circular arcs may represent a viable approach for producing sub-scale rocket nozzle contours, and that a further investigation is warranted between arc-based and existing full-scale rocket nozzles. Keywords Rocket nozzle · Supersonic flow · Contour design 1 Introduction 1. Sufficient thrust coefficient. 2. Ensure full-flowing engine operation at low altitude (suf- The increasing use of satellite

Journal

Shock WavesSpringer Journals

Published: May 28, 2018

References

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