Approximate Method for Calculating Transonic Flow About Lifting Wing-Body Configurations: Computer Program and User'S Manual

摘要

A user's manual is presented for a computer program which calculates inviscid flow about lifting configurations in the free-stream Mach-number range from zero to low supersonic. Angles of attack of the order of the configuration thickness-length ratio and less can be calculated. An approximate formulation was used which accounts for shock waves, leading-edge separation and wind-tunnel wall effects. (Author)