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Euler/Navier-Stokes calculations of transonic flow past fixed- and rotary-wing aircraft configurationsComputational fluid dynamics has an increasingly important role in the design and analysis of aircraft as computer hardware becomes faster and algorithms become more efficient. Progress is being made in two directions: more complex and realistic configurations are being treated and algorithms based on higher approximations to the complete Navier-Stokes equations are being developed. The literature indicates that linear panel methods can model detailed, realistic aircraft geometries in flow regimes where this approximation is valid. As algorithms including higher approximations to the Navier-Stokes equations are developed, computer resource requirements increase rapidly. Generation of suitable grids become more difficult and the number of grid points required to resolve flow features of interest increases. Recently, the development of large vector computers has enabled researchers to attempt more complex geometries with Euler and Navier-Stokes algorithms. The results of calculations for transonic flow about a typical transport and fighter wing-body configuration using thin layer Navier-Stokes equations are described along with flow about helicopter rotor blades using both Euler/Navier-Stokes equations.
Document ID
19890011577
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Deese, J. E. (McDonnell-Douglas Research Labs. Saint Louis, MO, United States)
Agarwal, R. K. (McDonnell-Douglas Research Labs. Saint Louis, MO, 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 2
Subject Category
Aerodynamics
Accession Number
89N20948
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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