A semi-span jet model is scheduled to be tested in NASA Langley’s 14-by-22 Foot Subsonic Wind Tunnel this winter to evaluate aircraft noise reduction technologies as part of the Flap and Landing Gear Noise Reduction Flight Experiment.
NASA Langley / Sean Smith
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Characteristics
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Data Acquisition
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Data Acquisition and Processing
Inputs: Analog, digital and electronically scanned pressure (ESP) system.
Controller: Open Architecture Data Acquisition Systems (OADAS)
Capacity / Channels: Analog: 128 / Digital: 32 / ESP module: 2,048
Dynamic Data Acquisition: 64 channels at up to 102.4 kilosamples/second based upon the VT1432b digitizer
Maximum Bandwidth: 46kHz, 24 bits for a 108db (typical) dynamic range
Classified Capability: Yes
Instrumentation
Strain Gauge Balances: 6-component internal
Available Corrections: Interactions, Temperature effects, Attitude tares, Axes orientation, Pressure tears, Momentum (flow) tares
Angle-of-Attack (AOA) Accelerometers: Q-Flex accelerometers
14-by-22-Foot Wind Tunnel Fact Sheet
