Methods are presented for calculating drag coefficients and average heating ratios for L/D ratios up to 20 and Mach numbers from 10 to 30. The cases of end-on, side-on, end-over-end tumbling, and random tumbling are covered for free-molecular and laminar continuum flow.

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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.

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