Combined with former numerical simulating results

vortex generators applicable for 2.4m transonic wind tunnel half-model test section were designed and validated to reduce side wall boundary layer effect. Results show that 20%-30% boundary layer thickness is reduced using trapezia-shaped flat vortex generators in subsonic conditions

and the influence on flow field uniformity is neglectable. The decrease of zero-lift drag and increase of lift-slope are found after vortex generators installation

meanwhile pressure center moves toward fuselage. Both trends are distinct evidence of thinner boundary layers. The developed vortex generators can be applied to half-model tests for subsonic conditions.