The reverse-flow theorem gives alternative integrals for generalized forces on oscillating wings by linearized theory. Applications to analytical and numerical solutions are discussed, and the latter are considered in some ...

Summary Independent numerical methods for obtaining the subsonic load distribution on a thin wing of arbitrary twist and camber have been developed at NPL, NLR (Netherlands) and BAC (Warton). The three methods have been ...

This note explains an improved numerical method of evaluating the contributions to the downwash at moderate or large spanwise distances from a vortex lattice. By allowing freedom of choice of ihe chordwise positions of the ...

An approximate theoretical formula for the distribution of aerodynamic load over arbitrary thick wings in incompressible flow is developed by combining three-dimensional results from thin-wing theory with twodimensional ...

There is a great need for more accurate data on the aerodynamic derivatives of swept-back wings in order to solve problems of stability, control and flutter. As one step in the search for these data the estimation of the ...

Leading-edge separation from fairly thin wings of moderate or low aspect ratio gives rise to aerodynamic loading and forces that are non-linear with incidence. It is important to be able to estimate these effects theoretically ...

Summary. A brief review of oscillatory theories reveals that some of these suffer from a defect that has been corrected in the Algol programme now subject to critical examination. Its features in steady and low-frequency ...

Extensive tables are given of pressure coefficients measured at Reynolds numbers from 1.3 x 10power6 to 3.9 x 10power6 on two half-models of identical planform with 5% RAE 101 and 9% RAE 101 streamwise sections. The planform ...

The theoretical method presented here gives improved accuracy and economy of operation, because it is modelled on a very satisfactory method for steady subsonic flow and is programmed in an efficient machine code for the ...

The report describes a theoretical investigation in support of measurements being made on an oscillating half-wing model of the plan-form shown in Fig. 1 in the National Physical Laboratory 25 in. by 20 in. Wind Tunnel ...