NASA NTRS · 19780005133
Self streamlining wind tunnel: Low speed testing and transonic test section design
Abstract
Comprehensive aerodynamic data on an airfoil section were obtained through a wide range of angles of attack, both stalled and unstalled. Data were gathered using a self streamlining wind tunnel and were compared to results obtained on the same section in a conventional wind tunnel. The reduction of wall interference through streamline was demonstrated.
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Wolf, S. W. D., Goodyer, M. J.. 1977-10-01. Self streamlining wind tunnel: Low speed testing and transonic test section design. https://ntrs.nasa.gov/citations/19780005133
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