Generally, aircraft design consists of four important elements, i.e. aerodynamic analysis, structural analysis, stability & control analysis and propulsion analysis. This project focuses on the aerodynamic analysis. Clear discussion on the theoretical background is included in the Chapter 2. Whereas Chapter 3 shows researches and studies which are conducted by the aerodynamists. The requirements of low speed UAV (16km/h) have been determined in the early stage. Based on the requirements, a suitable airfoil, which is Eppler 61, is analyzed from the low speed airfoil set recommended by the aerodynamists. The airfoil is further analyzed with different approaches, such as Fluent and Xfoil. The intention is to study the aerodynamic characteristics. This is important before continue to the next stage: wing design configuration. g design configuration is then undergoes analysis and comparison with different approaches. In th The wing configuration is designed to meet the requirements. Suggestions from different aerodynamists are adapted in this project. The winis project, Advanced Aircraft Analysis (AAA) is the primary tool. It is found that the aerodynamic module of AAA produce an acceptable wing result when it is compared with the different approaches, namely empirical data, Xfoil and Fluent. The aerodynamic characteristics of wing are obtained from the AAA and provided to structural analyst. The responsibilities of structural analyst are structural analysis and design of the wing body. The final part of this project is analyzes the complete wing body and produce the aerodynamic characteristics and derivatives, which are used for flight performance and stability analysis. This project found that AAA has poor prediction for low Re UAV (Re=15000) due to the limitation of AAA on the UAV below Re = 300000.
Aerodynamic analysis on low speed uav_Yap We Shee_A2_2012_NI