The method described utilizes a nonorthogonal coordinate system for boundary-layer calculations It includes a geometry program that represents the wing analytically, and a velocity program that computes the external velocity components from a given experimental pressure distribution when the external velocity distribution is not computed theoretically The boundary layer method is general, however, and can also be used for an external velocity distribution computed theoretically Several test cases were computed by this method and the results were checked with other numerical calculations and with experiments when available A typical computation time (CPU) on an IBM 370/165 computer for one surface of a wing which roughly consist of 30 spanwise stations and 25 streamwise stations, with 30 points across the boundary layer is less than 30 seconds for an incompressible flow and a little more for a compressible flow

/pdf/a-general-method-for-calculating-three-dimensional-2yd80hklgd.pdf

A general method for calculating three-dimensional compressible laminar and turbulent boundary layers on arbitrary wings

An accurate solution of the three-dimensional boundary layer equations over general configurations such as those encountered in aircraft and space shuttle design requires a very efficient, fast, and accurate numerical method with suitable turbulence models for the Reynolds stresses. The efficiency, speed, and accuracy of a three-dimensional numerical method together with the turbulence models for the Reynolds stresses are examined. The numerical method is the implicit two-point finite difference approach (Box Method) developed by Keller and applied to the boundary layer equations by Keller and Cebeci. In addition, a study of some of the problems that may arise in the solution of these equations for three-dimensional boundary layer flows over general configurations.

Some problems of the calculation of three-dimensional boundary layer flows on general configurations

Description of computer program for solving two dimensional and axisymmetric forms of compressible boundary layer equations for continuity, mean momentum, and mean total enthalpy

/pdf/computer-program-for-compressible-laminar-or-turbulent-28306hq8ea.pdf

Computer program for compressible laminar or turbulent nonsimilar boundary layers

: An analytical approach toward numerical calculation of the three- dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three- dimensional turbulent boundary-layer equations in conjunction with a three- dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.

Analysis of the Three-Dimensional Compressible Turbulent Boundary Layer on a Sharp Cone at Incidence in Supersonic and Hypersonic Flow

Simple, yet reasonably accurate, expressions have been developed for the prediction of skin friction and heat transfer coefficient at an infinite swept attachment line using the concepts of ‘reference temperature’ and ‘Reynolds analogy’. The formulae have then been used to investigate the effect of varying sweep angle with constant undisturbed free stream conditions in the limits of very low and very high Mach number.

Skin Friction and Heat Transfer at an Infinite Swept Attachment Line

Finite difference method for solving equations for compressible turbulent boundary layers on swept infinite cylinders

/pdf/the-compressible-turbulent-boundary-layer-on-a-blunt-swept-2g8emmgpnk.pdf

The compressible turbulent boundary layer on a blunt swept slab with and without leading- edge blowing

Finite difference solution for compressible turbulent boundary layer equations of swept slab with leading edge blowing

Finite-difference analysis of the compressible turbulent boundary layer on a blunt swept slab with leading-edge blowing

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The compressible turbulent boundary layer on a blunt swept slab with and without leading- edge blowing

Finite-difference analysis of the compressible turbulent boundary layer on a blunt swept slab with leading-edge blowing