32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, 13-17 June 2016, Washington, D.C., USA
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.
American Institute of Aeronautics and Astronautics
32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference.