33th Congress of the International Council of the Aeronautical Sciences

03.2 - Experimental Aerodynamics


T.D. Nguyenč, M. Taguchič, M. Kashitanič, K. Kusunose, Formerly Japan Aerospace Exploration Agency, Japan; čNational Defense Academy of Japan, Japan

In this paper, the effects of leading-edge flaps and trailing-edge flaps on the low-speed performance of supersonic Busemann biplane are clarified by wind tunnel tests and CFD simulations. Also, the staggering wing incorporated flaps also investigated. The measured system measures consist of the three-component balance system and a turntable, designed in the test section's sidewall. The position of the hinges of flaps is 0.3 times of chord length away from the leading edge and trailing edges. The stagger is set of 0.25 and 0.5 times of chord length. The results of single configurations showed the increment of lift and drag when flaps are installed. The lift slopes are nearly constant in the case of upper elements with the deflection of trailing flap lower than 30°. In cases of the lower element, the lift slope decreases when the deflection of the trailing-edge flap increases. The leading-edge flap makes the lift slope increase in both upper and lower elements. The results of biplane configurations show the increment in lift and drag when flap installed, as results of conventional monoplane wing. The results of the Busemann biplane (baseline configuration) show a good agreement with references and CFD data. When a trailing-edge flap is installed, the lift slope decreases when the deflection of the trailing flap increases. Also, the proportion of lower element to total lift and drag decreases when deflection increases at the angle of attack larger than 0°. The leading-edge flap and the stagger make the lift slope increase. Both flaps and stagger also make the maximum lift increase and decrease the stall angle compared with the baseline model. The stagger also makes the proportion of lower wing to total lift and drag decrease at the angle of attack larger than 0°.

View Paper