Program for calculation of maximum lift coefficient of plain aerofoils and wings at subsonic speeds.
Abstract:ESDU 93015 introduces a Fortran program for aerofoils and wings without high-lift devices. For aerofoils the method of ESDU 84026 is used, which itself relies on the prediction of lift-curve slope from ESDU Aero W.01.01.05. Sections can have a rough leading-edge (such as would result from ice formation) or a smooth leading-edge. The program applies a test to the section geometry data to determine whether the section has rear loading and trailing-edge thickness; such modern aerofoils have a higher maximum lift. If the user has not specified the section is modern, and the test shows that it is, the program will compute on that basis and print a warning. For wings the method of ESDU 89034 is used and assumes smooth leading-edges. The program first finds the spanwise location of peak loading for the given planform at each Mach number. The section geometry at each of those locations is then input, together with a camber and twist distribution which may be linear or non-linear. In the latter case aerofoil data are also required at the wing root and at 2/3 of span to calculate the zero lift incidence at those two sections. The input and output formats are fully explained and illustrated with worked examples.
|Data Item ESDU 93015|
This program is only available to subscribers.