A wind tunnel test was conducted to compare the characteristics of low speed stability and control for aircraft with conventional tail and V-tail configurations. Comparison was made in terms of static directional stability at selected test speed of 40 m/s, which corresponds to Reynolds number of 0.1622 x 106 based on the chord. Three types of simplified tail-only model were tested in Universiti Teknologi Malaysia's Low Speed Wind Tunnel (UTM-LST). Results show that the V-tail configuration greatly affects the aerodynamic characteristics in directional stability as the side force and yaw moment tends to vary linearly with yaw angles up to 25 degrees, compared to conventional tail that has linear characteristics up to only 10 degrees yaw

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This study is aimed to control unstable platform by introducing control system design through low-cost test rig for two rotor system with a feedback control.  The rig is used to control the bank angle by adjusting the thrust from each rotor and useful as a teaching aid in control system design.  In this paper, the transfer functions of the dynamic system for the two rotor platform was derived and introduce into the controller system. Inertia Measurement Unit (IMU) was installed to provide feedback to the control system.  MATLAB Simulink is used to simulate the response of the system before going to the real application while LabVIEW is used to interface the hardware interface and programmed the control system.