ESDU 69010 provides Stanton number data for the forced convection heat transfer between a two-dimensional laminar boundary layer and a smooth flat plate. Both local and mean values of Stanton number are given for a uniform wall temperature and zero pressure gradient in incompressible flow for Reynolds numbers based on distance from the leading-edge from 10000 to 100 million. The effects of Mach number, wall temperature and ambient temperature are also given for Mach numbers up to 5, ratios of wall temperature to recovery temperature from 0.2 to 2 and ambient temperatures of 100, 200, 216.5, 300 and 400 K. The data may be applied directly to axisymmetric flow over parallel circular cylinders and to the supersonic flow over two-dimensional wedges; they may also be applied to cones in supersonic flows with attached shocks by means of appropriate factors.