Methods for an analytic determination of the local coolant flow required to maintain a constant prescribed wall temperature for a transpiration-cooled gas-turbine blade are discussed. In the laminar-flow region, approximations for bodies of arbitrary shape obtained at NACA from wedge-type flow solutions are employed. In the turbulent-flow region, the Rannie-Friedman theory for a transpiration-cooled flat plate is used. Calculations for an arbitrarily chosen transpiration-cooled gas-turbine blade are presented. Recovery factors for a transpiration-cooled flat plate and verification of an existing method for correlating flow data for porous surfaces are included. Finally, a discussion of some of the difficulties associated with the problem of obtaining the proper local coolant flow is given.