The design of a passively combustor for a hypersonic tactical missile poses many severe structural problems whose solutions are beyond the current state of the art. To design such a combustor, the designer must predict accurately the erosion rate of candidate materials so that a realistic balance can be achieved among weight, performance, and cost. To make these predictions, basic experimental data must be taken to determine ablation rates as a function of surface temperature, pressure, gas flow rate, and gas composition. An experimental procedure has been developed to obtain this information for graphite materials exposed to various gases, such as CO, CO2, argon, and H2O, and simulated Shelldyne H-air combustion products. The data agree well with data obtained from the literature and indicate that at temperatures above 3500 degrees F the ablation rate is diffusion limited, CO2 in the stream reacts with carbon at the surface to form CO, and water vapor reacts with the surface (this was not anticipated prior to the tests). At 2000 degrees F, ablation is controlled by reaction rate, and both CO2 and water vapor in the stream react with the surface.
Graphite ablation in several gas environments
Graphitablation bei Lenkwaffen in verschiedenen Gasumfeldern
US Government Reports ; Jan ; 1-40
1983
40 Seiten
Report
English
Graphite ablation in high-pressure environments
AIAA | 1968
|Graphite ablation chemistry nonequilibrium effects
AIAA | 1975
|