Benchmark determination of Shuttle Orbiter entry aerodynamic heat-transfer data

Entry aerodynamic heat-transfer data were determined from the first flight of the Space Shuttle Orbiter. The convective heating rate data result from a rigorous mathematical analysis of one-dimension al, transient heat conduction within the orbiter thermal protection system (TPS) and reradiation from its surface during entry. Temperatures measured at the TPS surface during orbiter entry provide a surface boundary condition for the analysis. The rigorous mathematical treatment provides for a "benchmark" determination of in-flight convective heat-transfer rates. The source of the entry thermal data, the mathematical analysis technique, and the TPS thermal models are discussed. Typical convective heating rate data from the STS-1 mission are presented. cp GMT k NBS q #conv #rerad STS T Ts t x XI L e X p Nomenclature specific heat Greenwich mean time thermal conductivity National Bureau of Standards heating rate convective heating rate reradiated heating rate (eaT*) Space Transportation System temperature surface temperature = depth dimension - nondimensional body length = emissivity = thickness = density a . = Stephan-Boltzmann constant