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An experimental investigation of the static pressure fluctuation generation mechanism was performed for different transonic wind tunnel test section perforated wall configurations. Different hole diameters and geometrical configurations were investigated. Most tests were carried out with isolated perforations, while some were done with a three hole, 16 ~ perforation pattern. To suppress the oscillation amplitudes generated by perforations, splitter-plates as flow conditioning devices along the perforations were implemented on a large number of perforated transonic test section wall samples. It was found that all the hole configurations tested, regardless of diameter or shape, resonate at discrete frequencies which order themselves along several modes.

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