This study outlines the results of experimental research on flow parameters (flow angularity and static pressure) near a perforated wall using a six-hole probe located on the wall of T-128 wind tunnel test section in the area of significant perturbation caused by the model. In test section 1 the probe was set on the upper and lower walls (during the tests of a full-scale model); in test section 2 - on the side wall (during the tests of a half model). The perforation ratio varied from f=2% to f=10%. The distance between the perforated wall and the probe varied from 70 mm to 200 mm in order to detect the position where the probe is above the boundary layer. Technique to process acquired experimental data and to determine porosity coefficient R was developed and described in detail. A particular care was taken to study perforation f=6% since it is considered as an optimality state in terms of minimizing flow boundary interference in subsonic tests. All the measurements were made during industrial tests of various models in a wide range of subsonic speeds 0.2≤M≤0.95. The introduction includes the review of works on the topic. The study provides examples of flow computation near perforated walls of wind tunnel test section for the tests of flight vehicle models using acquired boundary condition parameters.
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