Due to the impulsion of aircraft manufacturers, Carbon Fiber Reinforced Polymers have become thicker. But the manufacturing process still implies the development of important residual stresses, either due to moisture effects or thermal effects [I]. If the symmetry of the composite part is broken, the global part shape will be affected by any moisture/temperature variation. In this communication, a simple L thick composite shell is studied under moderate temperature changes. An error in the stacking sequence is voluntarily added to the sequence in order to simulate possible manufacturing error. Displacements are recorded on the shell front and on its side using a mixed in-plane and out-of-plane DSPI set-up [8] The zone of interest is limited here to the central part of the L shape i.e. where the curvature is significant. Variations of the L-shape with temperature are recorded; typical flexure strain effects are outlined. Interesting global or local parameters can be deduced from this experiment: through thickness coefficient of thermal expansion, ply thickness and consequently local fiber volume fraction.