Description
Six-component supersonic wind tunnel tests were carried out on a 1/80 scale model of the C-105 aircraft at four Mach numbers. In all, 27 model configurations were investigated over a period of three months requiring a total of 1991 tunnel runs. This memorandum contains the results of these tests in the form of basic plots, cross plots and final aerodynamic derivatives. In order to expedite the publication of the data, the results are presented without detailed analysis.
