ESDU 98011 gives a method for predicting the viscous zero-lift incidence of aerofoils. The method applies to aerofoils with simple or complex camber lines and accounts for the effect of compressibility@ but is limited to subcritical flows. The boundary layer thicknesses at the trailing edge increase the zero-lift incidence above that predicted by inviscid theory. The method of Pankhurst is used to calculate the inviscid zero-lift incidence and two simple factors presented graphically are used to correct that value for the effects of viscosity and compressibility; both depend on the camber-line geometry in the vicinity of the trailing edge and Reynolds number while the latter also depends on Mach number. The VGK program was applied to a selection of aerofoils with a wide variety of camber-line shapes to derive the factors. The method applies to fully-attached flow and will therefore be unreliable for aerofoils with excessive thickness or camber. The accuracy of prediction of the viscous zero-lift incidence is within 0.2 degrees. Worked examples illustrate the use of the method.