전진익형 항공기 공력특성 증진을 위한 풍동시험

Wind tunnel test of an airplane model With forward swept wing was done in KARl LSWT to evaluate and measure the aerodynamic characteristics of Initially designed configuration Since the given wing planform did not fully satisfy the design requirements, local flow control devices such as vortilon, vortex generator and flow fence were used to delay separation and to enhance aerodynamic characteristics Also decision making processes of design parameters such as vertical tail boom length, the location, size and the incidence angle of honzontal tail were discussed The general aerodynamic characteristics of forward swept wing for various control surface deflection conditions of flap, aileron and elevator were also given.