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A Computational Investigation of Icing Effects on an S-Duct Inlet

A Computational Investigation of Icing Effects on an S-Duct Inlet effects of a typical glaze ice accretion shape on performance of M 2 1 2 9 S-duct inlet are computationally investigated for a range of flight s. A Reynolds-Averaged Navier-Stokes ( R A N S ) code with k-o> turbulence glaze ice accretion on cowl lip is A reduction of 2 2 . 8 % in total pressure massive flow model is used to simulate compressible viscous flow in S-duct inlet. modeled on a steady-state basis from N A S A L E W I C E 3 D code. T h e results show that total pressure recovery is reduced and compressor face distortion level is increased with flight . recovery is calculated for a flight of 0.85 in fully-developed glazed ice condition. separations in inlet induced by glaze ice horn shapes also create a mass flow reduction in inlet between 27 and 3 3 % as compared to clean inlet for flight s of 0.13 and 0.475, respectively. c o m b i n e d effects of reduced total pressure recovery and reduced mass flow rate results in a reduction of engine thrust between ~ 3 0 and 6 0 % from low speed flight http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Turbo & Jet-Engines de Gruyter

A Computational Investigation of Icing Effects on an S-Duct Inlet

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Publisher
de Gruyter
Copyright
Copyright © 2010 by the
ISSN
0334-0082
eISSN
2191-0332
DOI
10.1515/TJJ.2010.27.3-4.277
Publisher site
See Article on Publisher Site

Abstract

effects of a typical glaze ice accretion shape on performance of M 2 1 2 9 S-duct inlet are computationally investigated for a range of flight s. A Reynolds-Averaged Navier-Stokes ( R A N S ) code with k-o> turbulence glaze ice accretion on cowl lip is A reduction of 2 2 . 8 % in total pressure massive flow model is used to simulate compressible viscous flow in S-duct inlet. modeled on a steady-state basis from N A S A L E W I C E 3 D code. T h e results show that total pressure recovery is reduced and compressor face distortion level is increased with flight . recovery is calculated for a flight of 0.85 in fully-developed glazed ice condition. separations in inlet induced by glaze ice horn shapes also create a mass flow reduction in inlet between 27 and 3 3 % as compared to clean inlet for flight s of 0.13 and 0.475, respectively. c o m b i n e d effects of reduced total pressure recovery and reduced mass flow rate results in a reduction of engine thrust between ~ 3 0 and 6 0 % from low speed flight

Journal

International Journal of Turbo & Jet-Enginesde Gruyter

Published: Dec 1, 2010

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