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A flexible FORTRAN computer program to determine the temperature history and ablation history of aerodynamically heated flight bodies has been devised. The effect on heat conduction and aerodynamic heating histories of the removal of ablating wall materials is automatically accounted for by the computer program. The program is flexible in that it can accommodate flight body heat conduction inputs in the form of any reasonable combination of geometry and construction materials. The program will accept only one ablative material at any single position on the flight body surface but different ablative materials can be specified for different locations. One section of the program receives flight trajectory, radiation-property, and local aerodynamic flow inputs and provides for the computation of local aerodynamic heating and radiation relief. The other section of the program governs the computation of temperature history throughout the flight body and the thickness history of ablating layers. There is no provision for readjusting vehicle aerodynamics in accordance with body- shape changes.