Static aeroelastic effects of wind tunnel model on aerodynamic forces

Based on a model deformation videomeasuring system, a method was presented to investigate static aeroelastic effects on aerodynamic forces based on a model deformation videomeasuring system and computational fluid dynamic. Static aeroelastic deformation of wing tunnel model under aerodynamic loads was measured by the system and was used to drive the original model surface mesh to move to get deformed surface mesh for CFD. Then CFD results of aerodynamic forces on original shape and deformed shape were acquired to investigate the static aeroelastic effects. Analysis on deformation measurements and computational results of a high aspect ratio joined wing shows that the maximum lift coefficient variation occurs near the maximum attack angle in linear region of lift force while the maximum drag coefficient variation occurs near the stall angle. The variation of aerodynamic forces caused by static aeroelastic deformation is far beyond the precision target set for wind tunnel aerodynamic forces tests. So, it is quite necessary to investigate and modify static aeroelastic effects of wind tunnel model on aerodynamic forces.