Abstract:

ESDU 78010 gives charts of lift coefficient as a function of Mach number and thickness/chord ratio for a family of aerofoils having a particular form of supercritical upper-surface pressure distribution obtained by adding a local Mach number increment to the flat roof-top portion of pressure distribution used for the aerofoils of ESDU 71019. The charts give realistic design targets for drag-rise Mach number, lift coefficient at drag rise and thickness/chord ratio as well as providing exchange rates between those quantities. The chordwise station (coincidental with shock location) at which pressure recovery to the trailing-edge begins is treated as a variable. Thresholds corresponding to the onset of rear separation, attributable to the pressure rise from the shock-upstream location to the trailing edge, are predicted by a modified form of Stratford's criterion.