The development of detached shock waves ahead of wedges of 10° and 180° total angle has been studied for Mach Numbers of 1.04 and 1.15. It has been found that (i) in the early state of development the process of development is considerably influenced by wedge angle, (ii) the dependency of detached shock wave-shape upon wedge angle is less pronounced as the flow Mach Number approaches one, and (iii) in the absence of shock tube wall effect geometrically similar models having the same value of D/T₀ (non-dimensional delay time) produce similar shapes of detached shock waves for the same Mach Number.

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As a basic investigation on the swept-back wing plate of the high speed aeroplanes, the experiments on the elastic properties of the 30° swept back parallelogram wing plate with constant thickness in the two loading cases, i.e. (1) simple torsion, and (2) concentrated load were performed.
We analyzed the above two cases by S-R-S method in which the deflection function w(x, y) is assumed as follows,
and assured the good coincidence between the experimental results and the theoretical ones.
It is interesting to note in particular, that our analytical stress distribution agree well with the experiments, even when the swept back angle is 30°, and that the invariant-axis, which may be called by the elastic axis refered to the aerodynamic chord, can be found when the aspect ratio of the wing is rather large.

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In this paper a method for measurement of surface waviness by a checked plane and camera without any other optical systems is reported and methods of analysis are described.

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