Shock/Boundary-Layer Interaction Model for Three-Dimensional Transonic Flow Calculations

Mclean, J. D.; Matoi, Thomas K

doi:10.1007/978-3-642-82770-9_25

Cited by 5 publications

(1 citation statement)

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“…This is a three-dimensional finite difference formulation for both laminar and turbulent boundary layers. In addition, a semiempirical shock/boundary layer interaction model (McLean & Matoi 1986) has been added. Here, the treatment of the effects of a shock on the boundary layer is improved by replacing the boundary layer equations in the shock zone with a set of empirical jump conditions for the changes in the boundary layer quantities through the shock.…”

Section: Production Toolsmentioning

confidence: 99%

CFD codes and applications at boeing

Tinoco

1991

Sadhana

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The use of computational methods for three-dimensional flow design and analysis at the Boeing Company is presented. A range of computational "tools" consisting of "production" tools for everyday use by project engineers, "expert user" tools for special applications by computational researchers, and a new "emerging" tool which may see considerable use in the near future is described. These methods include full potential and Euler solvers, some coupled to three-dimensional boundary layer analysis methods, for transonic flow analysis about nacelle, wing/body, wing/body/strut/nacelle, and complete airplane configurations. As the examples presented show, such a tool box of codes is necessary for the variety of applications typical of an industrial environment. Such a tool box of codes makes possible aerodynamic advances not previously achievable in a timely manner, if at all.

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Section: Production Toolsmentioning

confidence: 99%