SUMMARYOF LAMINAR-BOUIIIMRY-LAYERSOLUIXONS FOR WEIX31&TKl?13FLOW

A summary of exact solutions of the laminar-boundary-layerequations for wedge-tyye flow, useful in estimating heat transfer to such arbitrar-ily shaped bodies as turbine blades, is presented. The solutions are de-termined for small.Mach nmbers and a Prandtl number at the wall of 0.7; ranges of mainstream pressure gradients and rates of coolant flow through a porous wall are considered for the following cases: (1) small tem-&=era-ture changes in the boundsry layer along a constant- and along a variable-temperature wall.,and (2) large temperature changes in the boundary layer along a constant-temperaturewall. Dimensionless forms of heat-transfer and friction parameters and boundary-layer thicknesses we tabulated. The results indicate that cool-ant emission and increased stream-to-walltemperature ratios diminished the friction and heat transfer for a constant wall temperature. For a variable wall temperature with small temperature differences in the bound-ary layer, the friction was unaffected, but the heat transfer was ~atl