Diagonal tension analysis of flat panels in shear is commonplace in aircraft design; such an analysis is presented in detail in the Royal Aeronautical Society Structures D.S., 02.03 series. In their present form, although well presented, they are time consuming and laborious to the engineer. It is therefore desirable to transform these data sheets into a form which can be easily programmed for solution by computers. The aim of this paper is to present such a format. The method is adequately covered in the data sheets, but important points are listed here. A step by step procedure for the analysis is given with a suggested programme input sheet and output format. An example is given with corresponding output data to be used for programme check-out purposes.