Conceptual Aircraft Empennage Design Based on Multidisciplinary Design Optimization Approach

Within a conventional aircraft design process, the horizontal tail and vertical are generally sized via volume coefficient methods. In this manuscript, an improved method for conceptual based on multidisciplinary optimization (MDO) approach with stability control constraints has been developed. To develop method, first, requirements have derived from regulations fundamental functionalities of plans. Then, empennage is formulated as MDO problem. Eventually combined wing. A test case presented concurrent wing plane design, which resulted in more than 9% reduction block fuel weight 3% maximal takeoff weight, indicates great potential burn carbon reductions at phase.