Wings are one of the main parts of the aircraft that serves to generate a lift force. Air wing shape affects the elevation that will be brought forth. Wing, which has the ability to produce lift large and efficient that has been developed by many aircraft designers. It was seen as more efficient carrying out of the annex, the aircraft can save fuel to be practiced. Likewise that the high aerodynamic performance is a prerequisite that an airplane. With hope we can learn the most effective angle to get the best performance of the annex. This research design and analysis of static on the airplane wing has an aspect ratio of 15.5 using Solidworks software and Patran / Nastran. Composite materials T300-N5208 become the main choice in designing the structure of the annexes of the aircraft where the laminae are arranged symmetrically with the fiber direction of 0 ° / 0 ° / 0 ° / 0 ° / 0 ° / 0 ° / 0 ° / 0 °, 45 ° / 45 ° / 45 ° / 45 ° / 45 ° / 45 ° / 45 ° / 45 °, 90 ° / 90 ° / 90 ° / 90 ° / 90 ° / 90 ° / 90 ° / 90 °, 0 ° / 45 ° / -45 ° / 90 ° / 90 ° / -45 ° / 45 ° / 0 ° and the thickness of the layer of 0.000125 per mm. In planning this study generated the force structure of the composite wing best on designing the fiber direction of 0 ° / 0 ° / 0 ° / 0 ° / 0 ° / 0 ° / 0 ° / 0 ° compared to fiber direction 45 ° / 45 ° / 45 ° / 45 ° / 45 ° / 45 ° / 45 ° / 45 °, 90 ° / 90 ° / 90 ° / 90 ° / 90 ° / 90 ° / 90 ° / 90 ° or 0 ° / 45 ° / -45 ° / 90 ° / 90 ° / -45 ° / 45 ° / 0 °.