1977•NASA Technical Reports Server (NASA)Requires access
Self streamlining wind tunnel: Low speed testing and transonic test section design
Stephen Wolf, M. J. Goodyer
Open publisher page 3 citations
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.