Abstract:
In modern aeroplane design a detailed knowledge of the behaviour of thin panels is very necessary. The problem of flat panels may be regarded as largely solved. This is not true, however, of curved panels and the object of this report is to obtain further information on the behaviour of curved panels under axial loading. The problem falls naturally into two parts, according as the Invesngat lon is concerned with the initial buckling of the panel or with its subsequent behaviour. The second part of the problem will be treated later, and attention is here confined to obtaining an accurate expression for the initial buckling stress of a slightly curved and perfectly fanned panel, the two straight edges of which are either simply supported or fixed.
