A general approach and tentative solution has been indicated to the problem of estimating wing skin thickness from preliminary design data. The solution is presented in a form that permits calculations to be made quickly and with a minimum of effort.

In deriving the empirical formula relating perimeter and area of the aerofoil section, only symmetrical sections were considered. The amount of camber normally employed, however, should not alter the results appreciably.

While the problem has been dealt with only partially and as yet only tentative empirical coefficients have been suggested, it is hoped that the author’s considerations of the problem will be of some interest and use at this stage.