Local Heat Transfer to Blunt Noses at High Supersonic Speeds

A brief summary is presented of the recent theoretical and experimental work on local heat-transfer rates on blunt-nose bodies. Comparisons of theoretical and measured heating rates indicate the following conclusions: The calculation of local conditions over noses of high radius of curvature needs more study and testing at the present time. If local flow conditions are known, the laminar heating rates over the whole nose shape can be calculated within most engineering accuracy requirements for the whole range of Mach numbers up to 13.8. For the case of turbulent flow, turbulent flat-plate theory based on local flow properties can provide good estimates of the heating rates possible. The prediction of transition remains at present the biggest unknown.