An experimental investigation was conducted in a Mach 5 free-jet tunnel to assess the problem of establishing supersonic flow with a high blockage model and to devise a modeltunnel test-section configuration which would allow flow establishment ("tunnel starting") at low pressure ratios. The model had a cross-sectional area equal to approximately 50 percent of the nozzle exit area. Two tunnel diffuser sizes with some combinations of model shroud configurations, and Mach 4 annular injectors at the nozzle exit and the diffuser entrance were investigated. Starting pressure ratios on the order of 50 and ratios of chamber pressure to free-stream static pressure of 1.0 were obtained during these tests
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