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Computational Analysis of the Effect of Porosity on Shock Cell Strength at CruiseA computational flow field analysis is presented of the effect of core cowl porosity on shock cell strength for a modern separate flow nozzle at cruise conditions. The goal of this study was to identify the primary physical mechanisms by which the application of porosity can reduce shock cell strength and hence the broadband shock associated noise. The flow is simulated by solving the asymptotically steady, compressible, Reynoldsaveraged Navier-Stokes equations on a structured grid using an implicit, up-wind, flux-difference splitting finite volume scheme. The standard two-equation k - epsilon turbulence model with a linear stress representation is used with the addition of a eddy viscosity dependence on total temperature gradient normalized by local turbulence length scale. Specific issues addressed in this study were the optimal area required to weaken a shock impinging on the core cowl surface and the optimal level of porosity and placement of porous areas for reduction of the overall shock cell strength downstream. Two configurations of porosity were found to reduce downstream shock strength by approximately 50%.
Document ID
20060023987
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Massey, Steven J. (Eagle Aeronautics, Inc. Hampton, VA, United States)
Elmiligui, Alaa A. (Analytical Services and Materials, Inc. Hampton, VA, United States)
Pao, S. Paul (NASA Langley Research Center Hampton, VA, United States)
Abdol-Hamid, Khaled S. (NASA Langley Research Center Hampton, VA, United States)
Hunter, Craig A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 23, 2013
Publication Date
May 1, 2006
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2006-2468
Meeting Information
Meeting: 12th AIAA/CEAS Aeroacoustics Conference
Location: Cambridge, MA
Country: United States
Start Date: May 8, 2006
End Date: May 10, 2006
Sponsors: National Oceanic and Atmospheric Administration, American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 581-02-08-07
Distribution Limits
Public
Copyright
Public Use Permitted.

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