The paper deals with the design and performance analysis of high wing of a Micro Class Unmanned Aerial Vehicle. The wing design involves its initial considerations like and weight of the aircraft, planform selection, selection of airfoil, area of the wing and wing loading characteristics. The design is done based on the calculated values and performance analysis is done to show airfoil characteristics, and performance of the wing with the help of XFLR5 software. The objective of this project is to compare the results obtained for different wing planforms, different angle of attack over a range of speeds. From the results we will conclude which wing configuration meets the payload lifting goals. Selection of wing configuration is an iterative process. The iterative process allows us to accommodate other design criteria such as catering storage, systems installations (high lift devices, attachment of motors and the main undercarriage) which may or may not be directly related to the goals of the mission. The result of iterative optimization is typically a compromise in configuration which best satisfies the overall needs of the mission. The final decision upon configuration will represent a compromise based on design priorities