Abstract
The design and characterization of an anechoic wind tunnel facility at the University of Florida are presented. A previously existing and ISO 3745 validated 100‐Hz anechoic chamber is upgraded to incorporate an open‐jet anechoic wind tunnel facility suitable for airframe noise studies, including swept‐wing trailing edge studies. For suitable modeling of landing conditions, a chord‐based Reynolds number of 3 to 4 million is required. The wind tunnel is driven by a 224‐kW centrifugal fan controlled by a variable frequency drive. The test section measures 0.74 m (29) by 1.12 m (44) by 1.83 m (6 ft). The estimated maximum velocity attainable in the test section is ∼ 76 m/s (250 ft/s). Preliminary measurements at 17 m/s indicate excellent flow uniformity and a turbulence intensity of 0.11%. Background noise level measurements with an empty test section reveal an overall SPL from 100 Hz 20 kHz of 49.9 dB, with a peak 1/3 octave‐band level of 46 dB at 100 Hz that decreases to 29.9 dB at 1 kHz. Facility characterization experiments over a range of test section speeds are also reported, along with the results of preliminary trailing edge noise experiments.
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