The 1.2m x 1.2m transonic test section of the INCAS Trisonic Wind Tunnel was designed 25 years ago by the Canadian company DSMA (now AIOLOS) in accordance with the state of the art technology of that time for interference ―free transonic testing (variable porosity walls with 60° inclined holes, self-ejection plenum chamber evacuation etc.). However. due to some technical deficiencies the results were not fully satisfactory: at Mach numbers higher than 1.0 the watt interference was important and the pitching moment values for tests with a calibration model differed from the interference-free results. Following thorough investigations the causes for the malfunction were identified and methods for correction were established and implemented. Tests with a cone-cylinder probe confirmed the improvement of the perforated wall wave cancellation properties and of the flow quality and transonic test section performances.
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