The deformations of the wing-sections and the stressed-skins of a high speed airplane will give a great effect on it's aerodynamic performance. In this second report based on the first report [1] already published, the deflection of a skin panel subjected to flight and thermal loads is analysed, and the equation with which the skin thickness needed to fulfil the requirements of allowance for the variations of a wing section can be calculated is presented. As one of the results, it is found that the aerodynamic requirements such that the forms of wing sections should be kept accurately within some allowance of deformation might often become considerably severe in the design of skin panel and the effect of elastic deformations should carefully be considered.

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The northerly turning error of the magnetic compass used in Aeronautics College, Miyazaki, is computed through Lindemann's procedure. Theoretical results are verified with the aid of flight tests. Next, the differential equation governing the northerly turning error is linearized in the initial stage of turning. For one example the approximate analytical solution thus obtained is compared with the exact solution and satisfactory agreement is observed. A number of similar aproximate solutions are constructed, and the dependence of various quantities characteristic to the northerly turning error upon the flight speed and the time rate of bank is clarified.

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