Flow-through Transducer for Wind Tunnel Analysis

About this technology

Overview

Existing integral flow-through balances have been limited to five-component force and moment measurements (Normal and Side force; Pitch, Yaw, and Rolling moment) – excluding a 6th desired force measurement: Axial force. To enable key aeroscience R&D applications, NASA’s Langley Research Center has developed a single-piece flow-through transducer design capable of measuring all six components – adding in the Axial force measurement. Compared to NASA’s technology, conventional flow-around designs (which require bellows and provide only a structurally parallel flow path around the balance) are typically restricted to low pressure applications; in contrast, NASA’s technology can accommodate both high- and low-pressure requirements, while eliminating the employment of bellows (which are complex to install and maintain, susceptible to leakage, highly flow sensitive, and lead to hysteresis effects). NASA’s rigid and stable integral flow-through balance offers repeatable and high-quality measurements that are significantly less dependent on pressure and flow rate affects.