A method for calculating laminar, transitional, and turbulent convective heat-transfer coefficients over the surfaces of turbine vanes is described. Results of calcu-lations with an approximate integral solution method are compared with results from a turbulent flat plate solution and a finite-difference solution.nThe approximate integral solution method produced heat-transfer coefficients in good agreement with the finite-difference solution method in the laminar and fully turbu¬lent flow regimes. The transitional flow regime length was approximately the same al¬though the regime began earlier for the finite-difference solution. The turbulent flat plate solution produced a conservative heat-transfer distribution which exceeded the finite-difference solution by as much as 150 percent.nThe calculations were made for given gas stream conditions of turbine inlet tem¬perature equal to 1273 K, turbine inlet pressure of 45. 7 newtons per square centimeter, a fuel/air ratio of 0.0, a vane channel inlet Mach number of 0. 31， and an exit Mach number of 0.84. Transition criteria were based on momentum thickness Reynolds num¬bers in the integral solution.
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