NASA Langley Wind Tunnel Winter Test: Data Acquisition Overview

The 14‑by‑22‑foot subsonic wind tunnel at NASA Langley is scheduled to test a semi‑span jet model during the winter as part of the Flap and Landing Gear Noise Reduction Flight Experiment. (Primary source)

Data Acquisition Configuration

Signal inputs include analog, digital, and electronically scanned pressure (ESP) systems, all managed by an Open Architecture Data Acquisition System (OADAS). (Primary source)

• The system supports 128 analog channels, 32 digital channels, and 2,048 ESP module channels. (Primary source)
• Dynamic data capture allows 64 channels to be sampled at up to 102.4 kilosamples per second using a VT1432b digitizer. (Primary source)
• The maximum bandwidth is 46 kHz with a 24‑bit resolution, yielding a typical 108 dB dynamic range. (Primary source)

Instrumentation and Corrections

Instrumentation includes six‑component internal strain gauge balances and Q‑Flex accelerometers for angle‑of‑attack measurement. Available corrections address interactions, temperature effects, attitude tares, axis orientation, pressure tears, and momentum (flow) tares. (Primary source)