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Numerical Investigation of Icing Effects on Dynamic Inlet Distortion

Numerical Investigation of Icing Effects on Dynamic Inlet Distortion The effect of the simulated ice accretion on the dynamic distortion of a diffusing S-duct inlet is numerically investigated. The LES turbulence model is used to simulate the unsteady flow separation and vortex shedding from the duct curvatures and ice accretion. The numerical methods for unsteady-flow solutions are validated with the wind-tunnel test data for dynamic inlet distortion. The results show that the protruding glaze ice horns create the strong vortex shedding structures that produce additional flow unsteadiness at the inlet engine face. In particular, the symmetrical glaze ice that uniformly covers the entire inlet lip increases the total pressure loss and fluctuation level more than the asymmetrical glaze ice with a less blockage to inlet flow. Furthermore, the symmetrical glaze iced inlet induces 17 times more severe instantaneous peak distortion than clean inlet at the free stream Mach number of 0.34. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical & Space Sciences Springer Journals

Numerical Investigation of Icing Effects on Dynamic Inlet Distortion

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Publisher
Springer Journals
Copyright
Copyright © 2018 by The Korean Society for Aeronautical & Space Sciences and Springer Nature Singapore Pte Ltd.
Subject
Engineering; Aerospace Technology and Astronautics; Fluid- and Aerodynamics
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-018-0044-0
Publisher site
See Article on Publisher Site

Abstract

The effect of the simulated ice accretion on the dynamic distortion of a diffusing S-duct inlet is numerically investigated. The LES turbulence model is used to simulate the unsteady flow separation and vortex shedding from the duct curvatures and ice accretion. The numerical methods for unsteady-flow solutions are validated with the wind-tunnel test data for dynamic inlet distortion. The results show that the protruding glaze ice horns create the strong vortex shedding structures that produce additional flow unsteadiness at the inlet engine face. In particular, the symmetrical glaze ice that uniformly covers the entire inlet lip increases the total pressure loss and fluctuation level more than the asymmetrical glaze ice with a less blockage to inlet flow. Furthermore, the symmetrical glaze iced inlet induces 17 times more severe instantaneous peak distortion than clean inlet at the free stream Mach number of 0.34.

Journal

International Journal of Aeronautical & Space Sciences – Springer Journals

Published: Jun 5, 2018

References

  • A computational investigation of icing effects on an S-Duct
    Jin, W; Taghavi, R; Farokhi, S
  • Measurement in a leading-edge separation bubble due to a simulated airfoil ice accretion
    Bragg, M; Khodadoust, A; Spring, S
  • Numerical analysis of an NACA 0012 airfoil with leading-edge ice accretion
    Potapczuk, M
  • Measurement in a leading-edge separation bubble due to a simulated airfoil ice accretion
    Bragg, M; Khodadoust, A; Spring, S
  • Aircraft Propulsion
    Farokhi, S
  • A study of three-dimensional turbulent boundary layer separation and vortex flow control using the reduced navier stokes equations
    Anderson, B; Farokhi, S
  • Turbulent Flow
    Pope, S