Propulsion Wind Tunnel 16T, located in the Propulsion Wind Tunnel Facility, provides flight vehicle developers with the aerodynamic, propulsion integration, and weapons integration test capabilities needed for accurate prediction of system performance. Large-scale models can be accommodated in the 16-foot-square, 40-foot long test section and be tested at Mach numbers from 0.05 to 1.60. Pressure in the test section can be varied to simulate unit Reynolds numbers from approximately 0.03 to 7.3 million per foot or altitude conditions from sea level to 76,000 feet. Air-breathing engine and rocket testing can also be performed in 16T using a scavenging system to remove exhaust from the flow stream.
Wind tunnel models can be supported in a variety of ways including a High Angle-of-Attack System for evaluating extreme flight attitudes and a Captive Trajectory Support system for weapons integration testing. Other testing support services include utilities for simulation of jet exhaust or control jets. A fuel system is also available for engine testing.
16T provides world-class test productivity by using automated and integrated test process controls. Modern steady-state and high-speed data systems with real-time displays and multi-channel remote controls are available. High-rate continuous-sweep data acquisition is routinely acquired to provide a more complete assessment of model aerodynamics and related effects during test. Through communication with the customer, AEDC can determine any other data needs.
Systems tested in 16T include: F-35 Lightning II, F/A-18E/F Super Hornet, B-2A Spirit stealth bomber, RQ-4 Global Hawk unmanned aerial vehicle, the Department of Defense's Evolved Expendable Launch Vehicle, the NASA Space Shuttle, the Blended Wing Body or the X-33 reusable launch vehicle.
16T has supported almost every major DoD and government flight vehicle program over the past 55 years. Customers utilizing 16T also include domestic and foreign private industry, and academia.