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      저자 : Kenichi RINOIE (검색결과 3 건)
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        Measurements of the Laminar-Separated Region on the Airfoil with Actively Deflected Flap

        Yuta Akama,Kenichi Rinoie 한국항공우주학회 2022 International Journal of Aeronautical and Space Sc Vol.23 No.4

        Recently, the study of flow around an airfoil at the low Reynolds numbers region has become increasingly important. At low Reynolds numbers, a laminar boundary layer separates from the airfoil and the laminar-separated region is formed. Previous studies demonstrated that deflecting the trailing-edge flap affects the flow downstream of the laminar-separated region. This study investigates flow pattern changes in the laminar-separated region when the flap deflection angle is dynamically altered. In this study, the NACA0012 airfoil (Re = 2.0×10^4) was used. The flap was attached at the trailing-edge, and the trailing-edge flap angle (δ) was changed from 5° to 20° at 0.5, 1, and 3 Hz (round trip) and from 10° to 30° at 0.5, 1, and 3 Hz (round trip). The velocity distributions around the airfoil were measured using time-resolved two-dimensional particle image velocimetry (PIV). It has been discovered that the larger the angle of attack and the flap angle, the larger the size of the vortex and the smaller the number of vortices emitted. The frequencies of the vortex emission when the flap is vibrated smoothly connect the results between the two cases where the flap angle is fixed. This suggests that when the flap is vibrated, the characteristics of the separated flow are highly dependent on the flap angle.

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        Estimation Method for Pitching Moment Non-linearities of Cranked Arrow Wing at Low Speed

        Hiroki Ishibashi,Taro Imamura,Kenichi Rinoie 한국항공우주학회 2022 International Journal of Aeronautical and Space Sc Vol.23 No.4

        Cranked arrow wing is a wing planform often used for supersonic transport (SST) to satisfy both low-speed characteristics during takeoff/landing and supersonic flight characteristics. During take-off and landing, an angle of attack (AoA) of the SST becomes high to generate sufficient lift. Leading-edge vortices generate additional lift (vortex lift) in such a situation. Additionally, vortex breakdown and outboard flow separation caused by the interference of leading-edge vortices occur. The wing’s aerodynamic forces change non-linearly with increasing AoA due to these phenomena. An estimation program based on potential flow for aerodynamic forces of the wing has been developed to investigate wing planforms and high-lift devices in past studies. The estimation program has three methods for modifying the results of potential flow to estimate the non-linear change of aerodynamic forces. In this study, a method to estimate the outboard flow separation is developed, and a method to estimate the vortex breakdown is improved to reduce differences between estimated and experimental results. By comparing estimated results using the present method with some experimental results, improvement of estimated results is observed.

      • Experimental Investigation of a Segmented Flap System of a Cranked-Arrow Wing

        Zhong LEI,Dong-Youn KWAK,Kentaro HIGUCHI,Kenichi RINOIE 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-

        A parametric study has been conducted for a segmented flap system of a cranked-arrow wing in a low-speed wind tunnel. The objectives were, (1) to develop design methodology for a multi-segment flap system. (2) to investigate the effect of leading- and trailing-edge flaps on the aerodynamic performance at take-off and landing conditions. (3) to construct database for design of high-lift. device, and (4) to validate the numerical simulation used for design. In this paper. effects of deflection angle of leading- and trailing-edge flaps on the aerodynamic performance will be discussed. Analysis of experimental data indicated that the segmented flaps were more effective than the uniform deflected flaps and an optimal combination of flap deflection angles had significant effects to improve the aerodynamic performance.

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