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AMTSACTResults of a variable-area diffuser investigatkm m the continuous IS-by lS-an. Naval Ordnance Laboratory Hypersonic Tunnel No. 4 are presented. A brief introduction discusses previous supersonic diffuse* work. The diffuser investigated and the eipcsuneutal technique are then described. The results show that air condensation in the test section at Ugh Mach Numbers'has only a minor effect on diffuser performance. Data on overall ptmmn ratios for starting and maintaining hypersonic flow for a number of diffusu configurations are presented. The test Mach Numbers rang* from 6.9 to 9A. Prom these data, a diffuser with a stagle-peaktd throat and a three-decree plane wall divergence aft of the throat was selected as most practical. The pressure lotwed by this optimum diffuse* varies, depending on Mach Number, from 1.8 to 2 3 times that movered by a pilot (or impact) tube operated at the teat section Mach Number. Data on pusstim diet rirwit inn measurements throughout the ooxzk and diffuser, spark scMlsrea photographs of diffuse* flow, and data on Reynolds Nusrher effects are also given. Finally, these data an oumpaiad with those of other investigator* and with