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The 3-D Euler and Navier-Stokes calculations for aircraft componentsAn explicit multistage Runge-Kutta type of time-stepping scheme is used for solving transonic flow past a transport type wing/fuselage configuration. Solutions for both Euler and Navier-Stokes equations are obtained for quantitative assessment of boundary layer interaction effects. The viscous solutions are obtained on both a medium resolution grid of approximately 270,000 points and a find grid of 460,000 points to assess the effects of grid density on the solution. Computed pressure distributions are compared with the experimental data.
Document ID
19890011579
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Vatsa, Veer N. (Vigyan Research Associates, Inc., Hampton VA., United States)
Wedan, Bruce W. (NASA Langley Research Center Hampton, VA, United States)
Turkel, Eli (Institute for Computer Applications in Science and Engineering Hampton, VA., United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1989
Publication Information
Publication: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
89N20950
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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