Revised and brought up to date by the inclusion of new gages, cemenbi, instrumentation, etc.-Ed.

The determination of the stresses in cemented lap joints has become of practical importance because of the development of new methods which permit a strong bond to be established between wood, plastic, or metal sheets, or combinations of them by the use of cement adhesives. In this paper, the problem is divided into two parts, (a) determination of the loads at the edges of the joint; (b) determination of the stresses in the joint due to the applied loads. Solutions are obtained for two limiting cases, i.e., where the cement layer is so thin that its effect on the flexibility of the joint may be neglected; and where the joint flexibility is mainly due to that of the cement layer. In both cases expressions are obtained for the shearing stresses in the cement, and for the normal stresses in the cement in a direction perpendicular to the plane of the joint.

The flutter speed of a uniform cantilever wing (one with a built-in root and with constant mass and stiffness characteristics along its entire span) is determined by integration of the differential equations for the wing motion. The solution is free of the dynamical approximations usually made during flutter analyses of the Rayleigh-Ritz type. A brief discussion of the procedures conventionally employed for the solution of the flutter problem is given, followed by a detailed derivation of the exact method for finding the flutter speed. It is found that a Rayleigh-Ritz type analysis, based on the fundamental uncoupled bending and torsion modes, is entirely adequate for the flutter analysis of a uniform wing. In addition to yielding a flutter speed which is in excellent agreement with the true value, the approximate method adequately predicts the wing shape at flutter. Additional parts of the paper deal with the relation between the uncoupled and the ground modes for the uniform wing, and with the nature of the wing response resulting from forced excitation while in flight.

A literature survey, including 314 references, is presented for the fields of automobile and airplane wheel shinu.The coverage is believed to be relatively complete insofar as the available, published world-wide literature is concerned. In addition to the bibliographic listings, a short review and appraisal of the contents of each reference is given.

Forming an extension of a previously published work (1), the present paper investigates the flutter of a uniform wing in free flight carrying a fuselage at its semispan and a weight at each wing tip. Wing-tip weights arise in practice when, for example, wing-tip fuel tanks are installed. The flutter system is studied by solving the differential equations for the wing motion. Solutions are carried out for two representative airplane configurations and the resultant speeds, frequencies, and mode shapes at flutter are compared with those obtained on the basis of conventional, Rayleigh-type flutter analyses. The methods of the original paper (1) are considerably refined, resulting in a significant reduction in the amount of labor required to effect a solution.