DESIGN OF AN ALL-COMPOSITE WING FROM CARBON FIBERS FOR SMALL TRANSPORT AIRCRAFT WITH MAXIMUM TAKEOFF WEIGHT UP TO 2000 KG

Abstract

Objective of this thesis is design of an all-composite wing from carbon fibers for small transport aircraft with maximum takeoff weight up to 2000 kg. The basic building formula is a certification specification CS 23. The thesis carries calculation of basic aerodynamic analysis of wing and its load. Furthermore is a read-in engineering design and FEM calculation.