Abstract
A parametric study is conducted on a segmented flap system of a cranked-arrow wing in a low-speed wind tunnel. The objectives are to investigate the effects of a multi-segmented flap system on the aerodynamic performance in takeoff and landing conditions, and construct a database for designing a high-lift device of a supersonic transport configuration. To achieve better aerodynamic performance, the leading-edge flap is divided into four segments, and the trailing-edge flap into two segments. In this paper, the effects of the deflection angle of flap segments on drag reduction and lift-to-drag ratio improvement are discussed for lift coefficients of interest. Analysis of experimental data indicates that the segmented flaps are more efficient than the uniform deflected flaps and an optimal combination of flap deflection angles enables larger improvement of the aerodynamic performance.
