No abstract

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.