衝撃波に關する研究

概要

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Many kinds of shock waves were tested by small pitot tubes, moving continuously along the stream. (1) Shock waves before the pitot tube. Small pitot tubes, diameter 1mm, were fixed in three Laval nozzles, which corresponded 1.5, 1.6, 2.1 in Mach number, and were 30×60mm in sectional dimension. Obtaining the Mach number from the pressure by the use of Rayleigh's formula, compared this with the result from the photographic method. We can conclude that the shock waves before the pitot tube agree exactly with the theoretical calculation. (2) Shock waves in Laval nozzles. In Laval nozzles appear shock waves, when the back pressure is not sufficiently low. These shock waves were tested by making small pitot tube pass through them. This results did not agree with the theory, especially in thickness and total head loss. But by investigating closely, we found that this depended on the separation of flow. (3) Shock waves on the Aerofoils. This type of shock waves were also accompanied with separation and differed from theoretical values, but had the same character with the second type.
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