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- W4240717210 abstract "An aerothermochemical model for the graphite nozzle erosion of the rocket motors was developed. The theoretical modeling of the problem is similar to the approach of Kuo and Keswani and the solution technique differs in modeling of the boundary layer over the nozzle. In this study, the integral formulation and solution of the boundary layer equations for highly accelerating flow in rocket nozzles derived by D.R. Bartz was used in the throat erosion calculations. The integral energy equation was modified by including heterogeneous wall reactions. It was assumed that the mass transfer Stanton number is equal to heat transfer Stanton number and diffusion controlled erosion was calculated accordingly. Predicted results showed good agreement with Geisler's experimental data and the theoretical predictions made by Kuo and Keswani. The integral method used in this study is found to be yielding the results faster than the differential method." @default.
- W4240717210 created "2022-05-12" @default.
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- W4240717210 date "1997-01-01" @default.
- W4240717210 modified "2023-09-26" @default.
- W4240717210 title "EVALUATION OF THERMOCHEMICAL EROSION OF THE SOLID PROPELLANT ROCKET GRAPHITE NOZZLE THROATS BY INTEGRAL BOUNDARY LAYER TECHNIQUE" @default.
- W4240717210 doi "https://doi.org/10.1615/intjenergeticmaterialschemprop..v4.i1-6.980" @default.
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