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Some of the methods used for obtaining quantitative aerodynamic heat-transfer data by means of temperature-sensitive coatings are described and discussed. A method whereby data can be obtained on arbitrary shapes without the use of a reference body has been developed. In this method, the heat-transfer coefficients depend only upon the thermal properties of the model material and the time required for a visible phase change of a fusible temperature indicator which is applied to the model as a thin surface coating. The phase change is recorded by motion-picture photography, and charts are given which relate the time required for the phase change to occur to the heat-transfer coefficient. Data obtained by this method are compared with aerodynamic theory and with data obtained by the conventional thermocouple-calorimeter technique. Several configurations were tested in the Langley Mach 8 variable-density tunnel. The results indicate that this method can be very useful and that accurate data can be obtained.