Studies on the High Temperature Oxidation of Molybdenum, Tungsten, Niobium, Tantalum, Titanium, and Zirconium

Fundamentals of Spacecraft Thermal Design

“…The correlation length a f was obtained by trial and error. Equations (12) and (13) were modified to account for the finite solid angle and programed on the computer. A trial-and-error procedure was followed to obtain the value of a 1 which best satisfied the experimental results.…”

“…CR-1420, 1969, NASA. 13 Streed, E. R., "The Influence of Temperature on the Stability of Low Solar Absorptance and Thermal Coatings," Proceedings of Conference on Spacecraft Coatings Development, TM X-56167, 1964, NASA, Washington, D.C. 14 Zerlaut, G. A., Carroll, ¥. F., and Gates, D. W., "Spacecraft Temperature-Control Coatings-Selection, Utilization and Problems Related to the Space Environment," Spacecraft Systems, Vol.…”

“…Comparisons between incidence angles for a given wavelength in each polar plot may be accomplished by noting the corresponding relative reflectances at 0 T = 0 in Figs. [13][14][15][16]. Also as may be noted in Figs.…”

“…The local solar intensity function can be evaluated from Eq. (13) and, in turn, local absorbed solar radiation follows from Eq. (11).…”

Isothermal and dynamic oxidation behaviour of Mo–W doped carbon-based coating

“…This is further supported by the strong presence of oxygen in the X-11 ray map as shown in figure 6b. At this temperature, Mo is almost depleted from the coating due to rapid evaporation of molybdenum oxides [13]. Furthermore as the onset of sublimation of tungsten oxide is at 750°C [14], the top surface of the oxide scale becomes depleted of tungsten.…”