Boeing Transonic Wind Tunnel
The Boeing Transonic Wind Tunnel (BTWT) delivers the best value for aerodynamic information to our customers in a safe, compliant and secure environment, making it one of the best facilities in the world.
The BTWT is a continuous-flow tunnel with a Mach range of Mach 0.3 to Mach 1.1. It has an 8-by-12-foot test section with 2-foot corner fillets; a dynamic pressure range from zero to 840 pounds per feet; controllable stagnation temperature and dew point; sting, swept strut, plate and floor mountings; internal and external balances; Electronic Pressure Scanning (EPS) up to 1,536 ports; and an inventory of EPS modules of appropriate load capacity and qualitative and quantitative flow imaging tools. An airflow facility is available for calibrating ducts and flow-through and powered nacelles.
Polysonic Wind Tunnel
The Polysonic Wind Tunnel (PSWT) is an integral part of new product development at Boeing. It can generate scale-model inlet and aerodynamic data in the subsonic, transonic and supersonic regime at various altitudes. It has two 4-by-4-foot test sections, one for supersonic and one for transonic and subsonic testing, and a new gas turbine compressor with double the pump rate of the previous compressor.
Applications include basic flow visualization, 2D contour plotting and pressure mapping onto 3D surface grids. Continuous shadowgraph systems, ultraviolet and oil flow equipment, and full photographic and closed-circuit television are available for all types of tests. A large family of primary model balances, miniature store balances and some specialized balances is available for almost any model application. Many ranges and types of conventional and ultra-miniature pressure transducers are available, and specialized equipment — including dynamic analyzers and videotape — can sense, record and analyze results.
Boeing Research Aero-Icing Tunnel
The Boeing Research Aero-Icing Tunnel (BRAIT) allows for aerodynamic testing of de-icing systems on the ground, saving you considerable time and resources over in-flight testing.
The test section is configured to enable extensive visual investigations in either the icing or the aerodynamics mode. The facility also has a spray-bar system that generates supercooled droplets upstream of the test section to create cloud simulations. Also available is heated auxiliary air to the test section and test article.
It also is possible to determine performance and calibrations under icing conditions and the effectiveness of anti-icing and de-icing systems. Ice shape molds can be made from ice formations built up on the test articles. Articles that can be tested include aircraft component sections, rotor-blade sections, and engine inlets and probes.
Low-Speed Aero acoustic Facility
The Low-Speed Aero acoustic Facility (LSAF) is powered by a 10,000-horsepower, fan-drive system, sending airflow past silencers, through a settling chamber and into our large anechoic chamber. The effect is a noise floor that is at least 10 decibels lower at most frequencies than any other wind tunnel in the world. With the low background noise levels, you can acquire data uncontaminated by competing background noise sources. The anechoic chamber can also be used for experiments that require low ambient noise and a free-field environment.
The LSAF is suitable for scale-model testing and for measuring noise and performance of aircraft model propulsion simulators, powered nacelles, airframes and other components. The facility also offers jet-airframe interaction testing and other special techniques. You can simultaneously conduct noise and performance testing, and our advanced six-component balance can measure forces of up to 6,000 pounds with an accuracy of 0.1%. Our scanning equipment and near-real-time information-handling system allow for run models with 400 channels of pressure and temperature instrumentation.