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The Icing Research Tunnel at NASA Glenn is the U.S.'s largest refrigerated wind tunnel. It is used to simulate natural icing conditions and test the effects of in-flight icing on various aircraft components and scale models.
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9- by 15-Foot Low-Speed Wind Tunnel
The 9- by 15-Foot Low-Speed Wind Tunnel at GRC has nationally recognized capabilities to evaluate the aerodynamic performance and acoustic characteristics of fans, nozzles, inlets, and propellers. The tunnel can simulate takeoff, approach, and landing in a continuous subsonic flow wind tunnel environment including the investigation of hot gas re-ingestion of short takeoff and vertical landing (STOVL) concepts. The acoustically treated test section and microphones linked to a dynamic data system allow state-of-the-art acoustic measurements to frequencies as low as 250 Hz for research in reducing aircraft noise. Recent programs supported in this facility include the High-Speed Civil Transport, the Advanced Tactical Fighter, as well as the General Electric Aircraft Engines (GEAE) next-generation (GEnx) engine.
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14- by 22-Foot Subsonic Tunnel
The 14- by 22-Foot Subsonic Tunnel at LaRC typically performs conventional performance testing for fixed-wing and rotorcraft configurations over a wide range of takeoff, landing, cruise, and high angle-of-attack conditions. However, this versatile facility can easily be reconfigured for acoustic, tethered free flight, forced oscillation (dynamic stability), and motor sports testing as well. The 14- by 22-foot tunnel also has the flexibility to test in either closed (walls, ceiling, and floor) or open (floor only) test section configurations. Recent upgrades to the facility automation system and fan motor (from 8000 to 12 000 hp) have greatly improved efficiency and capability. Major clients include the Department of Defense and aircraft manufacturers such as Boeing, Lockheed Martin, and Northrop Grumman.
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20-Foot Vertical Spin Tunnel
The 20-Foot Vertical Spin Tunnel at LaRC is the only wind tunnel in the Western Hemisphere configured for free-spin tests using the dynamically scaled model technique. This unique capability is used to significantly reduce risk during airplane flight tests by identifying potential spin modes, control techniques required for spin recovery, and spin chute size requirements. Other capabilities include static force and moment, surface pressures, rotary balance, and forced oscillation measurements. Recent tests include free-spin testing of a Generic Transport Model (GTM), rotary balance tests of the ARES Mars Airplane configuration, and free-fall dynamic stability tests of a lunar sample return atmospheric entry capsule. These are just a few of the projects conducted to support the vital missions of NASA, Federal agencies, and industry.
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Icing Research Tunnel
While there are numerous wind tunnels worldwide, the Icing Research Tunnel (IRT) is a rare and unusual facility located at GRC. Currently, the IRT is the U.S.'s largest refrigerated wind tunnel, devoted to investigating the myriad issues of aircraft icing. The tunnel simulates natural icing conditions to test the effects of in-flight icing on various aircraft components and scale models. The goal of the IRT is to replicate the Federal Aviation Administration (FAA) aircraft icing certification standards contained in the Federal Aviation Regulation (FAR) Part 25, appendix C. These tests reflect NASA's goals of assuring operational safety and advancement of critical aeronautics technologies to provide safer air transportation.
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