The analytical methods, computer-code techniques, and experimental test procedures used in the aerothermodynamic design of high-speed rockets are presented. The thermal protection system designed for the TalosTerrior-Recruit (TATER) rocket system is discussed. Comparisons between thermal response predictions and flight test experimental results for the TATER indicate that these methods can be used to design high performance rocket sytems.

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An aerothermodynamic analysis of the SNAP-27 LEM fuel cask is presented for each of three mission aborts. Aerodynamic models for point mass and six degree-offreedom trajectories are used, and the fuel cask heating rates and temperature responses are predicted for these trajectories. A survey of analytical and experimental studies of separated flow is related to the fuel cask, and a shock tunnel test program is outlined for further fuel cask analyses.