A simple method is given for the calculation of the heat transfer from a laminar flow surface. Computation is by a quadrature. The method is essentially a simplification and extension of the Eckert(1) method, and is applicable both to two–dimensional and to axisymmetric flows.

This Note Gives a simple relationship between the zero-lift wave drag of the wing of a rectangular wing and body combination and the wave drag of the portion of the gross wing blanketed by the body, both evaluated as if isolated (i.e. ignoring the interference of other parts of the combination). The result is valid only when the tip Mach cones of the wing lie downstream of the blanketed wing. Detailed results are given for the case of wings with double-wedge section, the maximum thickness being at mid-chord.

I wish to thank Mr. Wingham for his clearly relevant criticism of the proposed noseplane layout. I would suggest that the trouble which Mr. Wingham forsees might be avoided by mounting the noseplane as low as possible, as shown in the figure, with careful detail attention to engine positioning, alignment and air intake configuration. Also, the servo-plane would be relatively small and, trailing the air stream, cause little disturbance—surely, too, the high rear mounted mainplane now shown would exert a major smoothing effect on the general air flow pattern—per Jetstar and Caravelle?

Foster and Haynes recently suggested the possibility of measuring the rotary stability derivatives of an aeroplane by testing a suitably distorted model in a wind tunnel. This possibility has been examined for an isolated wing by the authors and has been found to be in error for the derivatives due to rolling and yawing.

In what follows it will be assumed that thin aerofoil theory and Prandtl’s lifting line theory may be applied.

In the bending and vibration of plates it is found that the values of maximum deflection and natural frequencies, respectively, vary considerably from the simply-supported to clamped edge conditions. For an estimation of these characteristics in the intermediate range a generalised boundary condition may be assumed, of which the simply-supported and clamped edges become limiting cases. While Bassali considers the ratio of edge moment to the cross-wise moment as a constant, Newmark, Lurie and Klein and other investigators, in their analyses of various structures, consider that moment and slope at an end are proportional.

Here the definition of elastic restraint as given by Timoshenko, α=βM, is followed, where α is the slope at any edge, M the corresponding edge moment per unit length while β is the elastic restraint factor. β→0 and β→∞ represent the two limiting cases of simply-supported and clamped edge conditions.