Abstract:
Summary. Section 1 gives some general concepts and definitions regarding heat transfer. In Section 2 a method is described for calculating the rates of heat transfer to the surface of an ideal flat plate or sharp cone in an airstream at Mach numbers up to 10, for both laminar and fully turbulent boundary layers. A system of predicting heat transfer to blunt-nosed bodies throughout the hypersonic speed range is given in Section 3, for laminar, transitional or turbulent boundary layers. The methods were previously described in data sheets which included comparisons with classified experimental results. These experimental data have been excluded from the present report in order to publish it in an unclassified form. It should be noted that no revision of the material presented has been done since 1962. Accordingly there may be parts of the report which have been out-dated to some extent by information published since that date.
