ESDU AERO W.01.01.07 gives curves of maximum lift coefficient of symmetrical aerofoils at Mach numbers of 0.60@ 0.70 and 0.75 as a function of the trailing-edge included angle and the thickness at 5 per cent chord aft of the leading-edge. The curves were obtained by correlating wind-tunnel test data at Reynolds numbers from 0.5E6 to 4E6 and the curves represent them to within about 0.1 in lift coefficient. The data are thought to apply to sharp-edged sections as well as rounded ones. Because of the complexity of the flow approaching stall it is stated that the curves are approximate and that they should only be applied to 'conventional aerofoils' with simple camber lines. It should not be applied to those with reflex camber and particularly not to those with large amounts of rear camber. ESDU 84026 should be used to obtain the maximum lift at Mach numbers up to 0.4.