The effect of the porous material characteristics on the internal heat and mass transfer.
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Engineering topics
Publications and source records attributed to Curry, D. M..
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Nonlinear least squares techniques can be used to determine effective thermal conductivity values from experimental data. Comparisons between measured and predicted conductivity values indicate that the analytically determined values can be used with confidence in performing thermal protection system analyses. A study was performed to compare the relative efficiencies of different minimizing techniques; the method of Peckham was the most efficient.
Analytical trade studies are presented that consider passive TPS configurations using the following material categories: (1) reuseable surface insulation - surface-coated rigidized ceramic fiber; (2) low density charring ablators; and (3) carbon-carbon and high density ablators for leading edge areas. Emphasized are effects on TPS weight by variations in entry trajectories and material thermal characteristics.
Nonlinear least squares techniques can be used to determine effective thermal conductivity values from experimental data. Comparisons between measured and predicted conductivity values indicate that the analytically determined values can be used with confidence in performing thermal protection system analyses. A study was performed to compare the relative efficiencies of different minimizing techniques; techniques; the method of Peckham was the most efficient.
A study was conducted to correlate Apollo ablation and thermal response flight data using advanced state-of-the-art analytical procedures. The agreement between flight data and predictions is consistently excellent for in-depth temperature distributions, char density profiles, and surface ablation, thus validating the analytical procedures.
Coupled nonlinear partial differential equations describing heat and mass transfer in a porous matrix are solved in finite difference form with the aid of a new iterative technique (the strongly implicit procedure). Example numerical results demonstrate the characteristics of heat and mass transport in a porous matrix such as a charring ablator. It is emphasized that multidimensional flow must be considered when predicting the thermal response of a porous material subjected to nonuniform boundary conditions.
Space shuttle thermal protection system optimal weight by numerical parameterization, discussing temperature constraints and material rearrangement effects
Performance prediction of fixed wing leading edges radiative, ablative and active cooling thermal protection systems and system weights comparison for space shuttle entry mission
Apollo ablator thermal performance at superorbital entry velocities
Reentry vehicle with multicomponent gas mixture injection, calculating heat and mass transfer correlations for stagnation point flow
Thermochemical and mechanical ablation mechanisms for Apollo heat shield material, comparing surface thermochemistry computer program and arc plasma tunnel data
Entry corridor thermal entry limits for Apollo spacecraft defined for design of thermal protection system
Thermal protection system for Apollo command module
Analytical model for predicting transient one- dimensional thermal performance of charring- ablator heat-protection system exposed to hyperthermal environment
Computer program for predicting charring ablation performance of heat shielding