The linear theory for a slender pointed body with zero attack angle in a hypersonic source flow is treated by using inviscid potential, theory, assuming that the hypersonic parameter is less than unity and that the ratio of specific heats is 2. The governing equation for source flow shows the similar form to that for parallel flow in the transformed co-ordinates system. Some numerical calculations for a cone and a cone-cylinder are presented, and the obtained surface pressure distributions are compared with the ones for the parallel on-coming flow. The comparison of the cone surface pressure shows that there is a considerable difference between parallel flow and source type one if the ratio of the source to body surface distance and the source to nose distance increases beyond about 1.1, while the comparison of the pressure along the cylinder part behind the nose cone shows that no essential difference could be seen between these two flows.
The angle of deflection of a flow passing through an oblique wire gauze was studied theoretically and experimentally. The deflections of flow were measured for five kinds of wire gauzes having different degrees of solidity at setting angles of 30 to 75 degrees, and these measured values were between 80 and 90% of the theoretical value. An application to divergent nozzles was also described, where flow observation and velocity-distribution measurement were carried out for a model divergent nozzle equipped with two oblique wire gauzes.
The generation of a kind of circulatory flow in the separated-flow region of a stalled sweptback wing was noticed. Observation on the circulatory flow was made for a model airplane by using evaported-gas-oil smoke. The presence of a strong lateral outward flow was observed in the considerable range behind the trailing edge of wing-root portions. The effect of the angle of sweep back and taper ratio of a wing on the intensity and direction of the circulatory flow were also investigated.
In general, thin-walled beams with open section have the defects that their torsional rigidity is very lower and their maximum shear stress for a given torsional moment is relatively larger than beams with closed section. To avoid this, the method of making theopening edges of the beams locally connected by spot welding or rivetting have been taken. For this instance, Fig. 1(a) shows a beam in which the narrow opening edges are locally welded. In Fig. 1(b), the wide opening edges are connected by transverse braces. In Fig. 1(c), the facing flange of the two beams with hat-type section are directly con-nected by spot welding. These beams were named by the authors as semi-closed beam. In this paper, it was proposed to apply general theory of torsion based on the simple torsion theory (solution of Saint Venant) to these semi-closed beams, among which the effects of spot pitch on torsional rigidity or criterion of failure, etc. was cleared. It was found that the the ory and experiments fairly coincided with each other comparatively with reasonable accuracy.
Following the preceding paper which dealt with the torsional properties of semi-closed section, in this paper, theory of bending, especially of shear center of these section is presented. The theory is based on Saint VENANT'Ssolution for bending and to introduced this solution in the theory, the basic assumption used in the previous paper is also applied. The result obtained is as follows; the shear center for a general cross section has a fixed position, but in the case of semi-closed section, it is fixed by the form of cross section and the pitch of connection at opening edges.