Development of a supersonic aerodynamic test section using computational modeling

*† The design of a supersonic aerodynamic test section was implemented using computational modeling. Initial two-dimensional computational flow simulations revealed critical design issues such as starting the test section and model placement. These issues were resolved to provide a test section capable of operating throughout the Mach number range of the tunnel, with reduced flow blockage and substantial optical access. The final test section inlet design, tunnel starting data and optical access are shown.

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