Effect of Stagger on Low-Speed Performance of Busemann Biplane Airfoil

In this study, the low-speed performances of Busemann biplane were clarified, focusing on relative contributions upper and lower elements to total aerodynamic characteristics biplane. Also, effects staggered biplane, which changes horizontal distance between two wings in a configuration, investigated by balance measurements numerical simulations. The flow velocity was 15 m/s, Reynolds number based airfoil chord length 2.1 × 105. tests integrated wing, attack angles wing varied system turntable, set wind tunnel sidewall. results show that element generated most lift drag (or baseline model with no stagger) at high attack. At above 20 deg, contribution is almost constant, 95% 88% drag. smaller than sum individual treated as single configuration. increments due stagger confirmed, especially When value increases, high-pressure area near leading edge surface also increases up-per element. This main reason for model. prevented leading-edge separation configuration increased slopes