So far, little is known of the effect of camber or twist on the pressure distribution and drag of a wing flying at supersonic speeds, but with subsonic leading edges. According to the linear theory, for a subsonic leading ...
Camber and twist is applied to the problem of reducing the drag due to incidence, of thin triangular or swept-back wings, at supersonic speeds, with subsonic leading edges and supersonic or sonic trailing edges. Two cases ...
Formulae for calculating the-gradients and ordinates of the camber surfaces of swept-back wings of arbitrary plan-form with subsonic leading edges, and specified load distribution, are given, including those which have ...
Formulae are found for the pressure distribution at supersonic speeds and at zero incidence for certain symmetrical surfaces of small finite thickness, with swept-back leading edges, the surfaces being set symmetrically ...
Some general solutions of the linearised equations of supersonic flow, in terms of Lamé functions, were obtained by G. M. Roper, using the methods of Robinson and Squire. The results were applied to calculate : (a) the ...
Camber and twist is applied to the problem of producing low-drag wings with no leading-edge pressure singularities, at design lift. The suction peaks near the leading edges of the wing are removed and the associated adverse ...