Accession Number : AD0445598


Title :   TECHNIQUES AND INSTRUMENTATION ASSOCIATED WITH ROCKET MODEL HEAT-TRANSFER INVESTIGATIONS


Corporate Author : ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)


Personal Author(s) : Rumsey, C B


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/445598.pdf


Report Date : Jul 1961


Pagination or Media Count : 33


Abstract : In the study of aerodynamic heat transfer and thermal protection by use of rocket-propelled models several factors must be considered. The over-all model configuration should fly at zero angle of attack although the model can be designed to provide heat-transfer measurements on bodies and surfaces at angle of attack. Different trajectories that could be obtained with the same rocket model provide quite different test conditions and the selected trajectory must be accurately predicted for design of the heat-transfer model. The instrumentation carried within the model is generally not extensive, but design of the skin as a calorimeter and the installation of thermocouples require particular attention. To determine the heat-transfer rate on a thermally-thick skin, the previous time history of skin temperature must be considered, and rapid fluctuations of the heating rate may be obscured. The instantaneous heating rate on a thermally-thin skin can be determined directly from the corresponding time rate of change of skin temperature.


Descriptors :   *ROCKET MODELS , NATO , ABLATION , SURFACE TEMPERATURE , SWEAT COOLING , THERMAL PROPERTIES , HEAT SHIELDS


Subject Categories : Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE