람다 날개 형상의 옆미끄럼각 효과에 대한 실험적 연구

Abstract

ABSTRACT An experimental study on aerodynamic coefficients of a lambda w ing configuration was performed at the low speed wind tunnel of Agency for Defense Development. The main purpose of this study was to investigate the effects of sidesli p angle on various aerodynamic coefficients. In the case of 0 ° sideslip angle, nose-up pitching moment rapidly increases at a specific angle of attack. This unstable pitching moment characteristic is referred to as pitch break or pitch up. As the sideslip angle increases, the pitch break is found to be generated at a higher angle of attack. Rolling mome nt is found to show similar behavior pattern to ‘pitch break’ style with angle of attack at non-zero sideslip angles. This trend gets severer at greater sideslip angles. Yawing moment also shows substantial variation of the slope and the unstable directional stability with sideslip angles at higher angles of attack. These characteristics of the three moments clearly implies the difficulty of the flight control which requires efficient contr ol augmentation system.