HORIZONTAL TAIL SIZING ANALYSIS WITH LONGITUDINAL STATIC AND DYNAMIC STABILITY EVALUATION APPROACH-CASE STUDY FIGHTER AIRCRAFT IF-X C103

• Main Author: JUNITU TIKUPASANG - NIM: 23616001, DOMINICUS
• Format: Theses
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/26749
• Institution: Institut Teknologi Bandung

<p align="justify">Horizontal tail of an aircraft is an important component of the aircraft in accomplishing its operation. Optimum horizontal tail design results in a good stability and control degree that meets the design requirement of the aircraft. <br /> <br /> A fighter aircraft that needs high maneuver with the range of speed from subsonic to supersonic requires stability design approach that is not similar to that of the conventional aircraft with low speed and low degree of maneuver. The such of speed range has the possibility of the aircraft static stability to increase during the aircraft speed increase. This is due to the aircraft neutral point (NP) tends to shift backward during speed increase that will result in high static stability at supersonic speed. <br /> <br /> High static stability degree will cause an aircraft to maneuver hardly at supersonic speed. This condition can be solved by applying aircraft design with relaxed static stability. In this design condition, it is possible of the aircraft to have less static stability, neutral, or even statically unstable at low speed. Horizontal tail design for the such of condition mostly put dynamic stability in consideration rather than static stability. Consideration of dynamic stability criterion in design process will result in optimal horizontal tail design. <br /> <br /> This thesis will evaluate a design process to determine horizontal tail dimension by considering longitudinal closed loop dynamic characteristics.<p align="justify"> <br />