A wing has an aspect ratio of 10, a taper ratio of 0.4, and a tip geometric twist of -3.5 degrees. The wing root section is an 18% cambered airfoil with a zero-lift angle of -1.5 degrees, while the tip is a 10% thick symmetrical airfoil. The 2D airfoil lift curve slope is constant from root to tip and has a value of 2*pi rad^-1. Calculate the wing lift coefficient at a wing angle of attack equal to 10.64 degrees (you may assume Ď„ = 0).