A Fully Automatic Combined Potential-Flow Boundary-Layer Procedure for Calculating Viscous Effects on the Lifts and Pressure Distributions of Arbitrary Three-Dimensional Configurations.

摘要

This report describes a method for calculating viscous effects on the lifts and pressure distributions of arbitrary three-dimensional configurations. The approach consists of combining a panel method,which calculates potential flow about arbitrary three-dimensional lifting configurations,with a boundary-layer method. Combined procedures have been constructed using a two-dimensional boundary-layer method in a strip-theory sense and using a three-dimensional small cross-flow boundary-layer method. Various fundamental and procedural aspects of the general calculation scheme are investigated and discussed. Final emphasis is on a completely automatic procedure that performs its calculations in a single computer run without intermediate human intervention. For this purpose the method based on a strip-theory boundary layer has proved very satisfactory. Calculated inviscid and viscous lift and pressure distributions are compared with experimental data for a variety of wings and wing-fuselages having both conventional and supercritical airfoil sections. The agreement of the viscous calculations with experiment appears to be quite good. (Author)