FLOW STUDIES IN A CONTOURED NOZZLE DESIGNED FOR A SMALL HELIUM HYPERSONIC WIND TUNNEL.
JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
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Pressure measurements were made in a contoured nozzle designed for a 2 in. Helium Hypersonic Wind Tunnel. This nozzle was designed to give a uniform Mach 18 flow at the test section. The investigation showed that the measured exit centerline Mach number was less than the design value and that a nonuniform flow existed in this region. These results were attributed to the boundary layer displacement thickness being considerably larger than estimated. Uniform Mach 14.7 flow was produced at a station about onethird of the nozzle length from the exit. The flow characteristics of this nozzle provide a basis for the evaluation of the techniques of estimating the viscous flow correction in small contoured nozzle. Author