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Computation of aircraft component flow fields at transonic Mach numbers using a three-dimensional Navier-Stokes algorithmA computer analysis was developed for calculating steady (or unsteady) three-dimensional aircraft component flow fields. This algorithm, called ENS3D, can compute the flow field for the following configurations: diffuser duct/thrust nozzle, isolated wing, isolated fuselage, wing/fuselage with or without integrated inlet and exhaust, nacelle/inlet, nacelle (fuselage) afterbody/exhaust jet, complete transport engine installation, and multicomponent configurations using zonal grid generation technique. Solutions can be obtained for subsonic, transonic, or hypersonic freestream speeds. The algorithm can solve either the Euler equations for inviscid flow, the thin shear layer Navier-Stokes equations for viscous flow, or the full Navier-Stokes equations for viscous flow. The flow field solution is determined on a body-fitted computational grid. A fully-implicit alternating direction implicit method is employed for the solution of the finite difference equations. For viscous computations, either a two layer eddy-viscosity turbulence model or the k-epsilon two equation transport model can be used to achieve mathematical closure.
Document ID
19890011562
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shrewsbury, George D. (Lockheed Aeronautical Systems Co. Marietta, GA, United States)
Vadyak, Joseph (Lockheed Aeronautical Systems Co. Marietta, GA, United States)
Schuster, David M. (Lockheed Aeronautical Systems Co. Marietta, GA, United States)
Smith, Marilyn J. (Lockheed Aeronautical Systems Co. Marietta, GA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1989
Publication Information
Publication: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1
Subject Category
Aerodynamics
Accession Number
89N20933
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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