A study was made of design techniques for low density wind tunnels operating with high stagnation temperatures and hypersonic flow.nAn approximate boundary layer analysis was developed tonpredict feasible ranges of operating conditions for low density wind tunnels.nDetailed calculations were made for three nozzles including boundary layer corrections for isentropic contours. It became obvious that the use of a high stagnation temperature wind tunnel for investigations of rarefied gas dynamics could produce situations in which it would not always be clear whether the experimental results were associated with rarefied gas flow phenomena or related to high temperature physical phenomena.nIt appears that unless an enormous amount of money is devoted to the construction of an extremely large low-density wind tunnel, it will never be feasible to test large models
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