| Abstract | This paper explores the use of CFD results as a benchmark to improve and validate the wall correction methodology currently applied in the National Research Council of Canada 1.5 m Trisonic Wind Tunnel. Particularly, it focuses on the update of the potential theory representation of the half-span model of a typical aircraft tested at this facility, which plays a significant role in the calculation of wall corrections. Firstly, a study of the current fuselage representation is carried out, showing its limitations. An updated potential theory fuselage representation is then presented and tested, showing a notable improvement compared to its predecessor, primarily at higher angles of attack. Next, the complete half-model potential theory representation is reviewed and its strengths and weaknesses are discussed. Finally, a CFD-based validation technique for the wall correction methodology is outlined, and correction results based on existing RANS simulations are presented. |
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