Spanwise Load Distribution Research Articles

Comments on "Limiting Circulatory Lift of a Wing of Finite Aspect Ratio"

The second point questions the direct application of Eq. (1) to the finite jet-flapped wing. In the derivation of Eq. (1), it is assumed tha t the wing has an elliptic spanwise loading distribution and tha t the trailing vorticity lies in a plane inclined to the free stream at the induced down wash angle calculated at the wing lifting line. But, the ultimate downwash angle far behind the wing will be twice the inclination at the wing. Thus, the effects of the curvature of the trailing vorticity in the stream direction are neglected. However, it is possible to include these effects by considering the forces on a control surface at infinit}^ in the usual manner. A wing, which has an elliptic load distribution given by r = r0(i v A) (2)

The Distribution of Lift over the Surface of Swept Wings

SummaryA simple method is given for calculating, in incompressible flow, the spanwise and chordwise loadings on thin swept wings with symmetrical aerofoil sections and of moderate and large aspect ratios. The present note is based on, and continues, the investigation described in an earlier paper. The design of swept wings with given spanwise and chordwise load distributions, obtained by modifying the plan form of the wing or by adding camber and twist, is briefly considered, as well as the design of swept wings which give minimum induced drag.