Stresses in the covers of torsion boxes containing large cutouts are found by changing half of the symmetrical uncut portion of the cover into three stringers c

A method is presented for calculating the stresses produced by rectangular cutouts of any size in torsion boxes. The problem is divided into a "box problem" and

A method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon l