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FAILURE of panels under static compression, or for that matter under any loads, involves a vast array of problems ranging from properties of material to initial instability and post‐buckling phenomena as occurring in various types of panels. It is not intended here to do justice to all these aspects of the subject but to select a single—but at the same time very important—topic, develop its analysis as fully as possible, and present the results in a readily applicable form. The structure investigated is the single skin stiffened panel under compression and the mode of failure considered, denoted by flexural cum torsional failure, involves predominantly flexure and torsion of the stringer with a wavelength of greater order of magnitude than stringer height and pitch. By torsional deformation of the stringer we understand a rotation of its undistorted cross‐section about a longitudinal axis R in the plane of the plate, the position of which will be selected later on (see FIG. 1b). The panel may, of course, also fail in a local mode of stringer and plate with a short wave‐length of the order of magnitude of stringer height and pitch, but the analysis of this case is not included here (see, however, Argyris and Dunne). Note that a local mode of deformation of a stringer formed by straight walls is commonly defined as a distortion of the cross‐section in which the longitudinal edges where two adjacent walls meet remain straight (see FIG. 1c).

WE define as an open tube a thin‐walled structure, the cross‐section of which does not include any closed circuit. This property is common, for example, to the curved channel, the interspar wing cut‐out and the panel stiffened with Z‐sections, illustrated in FIG. 1 (a, b, c). But the interspar cut‐out with nose cell (FIG. 1d) is not an open tube in the present definition. All structures discussed in this paper are assumed to be cylindrical and to have a constant cross‐section. It is relatively simple to extend the results to conical taper and longitudinally varying thickness, but this would be beyond the scope and space of the present analysis (see, however, ref. 5).

The methods developed in sections (5)–(7) are now applied to the determination of the torsional cum flexural failing stresses in two panels. The following points should be noted:

This issue is a selected bibliography covering the subject of leadership.

Despite the growing body of literature on both organizational learning (OL) and corporate venture development (CVD), very few attempts have been made to establish connections between these two literature streams. While existing literature provides some evidence that OL may facilitate the process of CVD, several interesting research issues remain unexamined. We know very little about (a) what type of learning processes are effective at various stages of CVD; and (b) whether and how knowledge created through various OL processes enhances venture performance. These research issues are examined in this paper by integrating the literature from OL and CVD. We develop a conceptual model that integrates organizational learning with the antecedents and outcomes of CVD. We argue that (a) organizational learning in CVD occurs through two distinct and yet complementary processes; (b) productive organizational learning occurs when organizations vary their emphases on different types of learning depending upon the stages of CVD; and (c ) different types of learning are associated with different types of venture outcomes. Propositions are developed and implications are discussed to facilitate empirical research.

To the Editor. DEAR SIR, I wish to make the following comments on the article entitled ‘The Open Tube’; AIRCRAFT ENGINEERING, Vol. XXVI, No. 302, April 1954, pp. 102–112, by Dr John Argyris.