CW-22 Facility Description
This facility is used to evaluate the aerodynamics and heat transfer characteristics of blade geometries for future turbine applications. Unique features combine the ability for a high degree of airflow turning, infinitely adjustable incidence angle, and high transonic flow rates. The facility air supply and exhaust pressures are controllable to 16.5 psia and 2 psia respectively. The inlet air temperatures are at ambient conditions. Air supplied from the 40 psig system passes through a 10µ air filter and a flow restricter to flow rates up to 55 lb/s. Air flows through a 108-in. diameter acoustically lined plenum chamber, transitions to a 48- by 72-in. rectangular cross section, and is flow-conditioned before entering the 48- by 6-in. contraction section to the test section designed for airfoils with a span of 6 in. The test section is equipped with boundary layer bleed. Airflow exhausts to the altitude exhaust system.

CW-22 Special Features
Incidence angle is achieved through the manual rotation of a large disk. The airfoils (currently at 10), inlet boards, and boundary layer bleeds are attached to and interposed between these disks. The airfoil angle of attack is achieved by rotating the disk to the desired incidence angle. A windowed section can be interchanged to allow for Laser Doppler Velocimeter measurements. Computer hardware allows for 256 analog channels and approximately 1500 other channels using an ESP system tied into the ESCORT D data acquisition system.