Has supported Ultra-Efficient Engine Technology (UEET), Quiet Aircraft Technology (QAT), Versatile Affordable Advanced Turbine Engine (VAATE), the JSF and the ATF.Maintains a series of drive rig systems to power engine fan models for performance and acoustic testing.Is the only national facility that can simulate takeoff, approach and landing in a continuous subsonic flow wind tunnel environment.Is the most utilized low-speed propulsion acoustic facility in the world.Take a virtual tour of our 9×15 Low-Speed Wind Tunnel.Name:ĩ- by 15-Foot Low-Speed Wind Tunnel (9×15) The facility is used to evaluate aerodynamic performance and acoustic characteristics of nozzles. The test section is 9 ft high by 15 feet wide by 33 feet long and provides airspeeds from 0 to 165 mph. The 9×15, housed in the return leg of the 8- by 6-Foot Supersonic Wind Tunnel (8×6), provides a unique facility for testing large-scale hardware in a continuous subsonic air stream. Variety of available research test hardware.750-hp (per shaft) counter-rotating drive rig system.1,000- and 5,000-hp fan drive rig systems.Advanced optical imagery (sheet lasers, pressure-sensitive paint (PSP), and temperature-sensitive paint (TSP)).A unique “rotor alone nacelle” test capability allows isolation of “fan alone noise” by elimination of outlet guide vanes. A series of drive rig systems are available to power engine fan models for performance and acoustic testing. The facility is acoustically treated and equipped with microphones linked to a dynamic data system. Advanced Ducted Propulsor (ADP) Fan Commissioning Test (front view) in the 9- by 15-Foot Low-Speed Wind Tunnel (9×15) Providing airspeeds from 0 to 165 mph, this facility has unique and nationally recognized capabilities to evaluate aerodynamic performance and acoustic characteristics of nozzles, inlets and propellers. Programs supported in this facility include a variety of commercial aircraft propulsion systems: the High Speed Civil Transport (HSCT), Advanced Tactical Fighter (ATF), Joint Strike Fighter (JSF) and other military short takeoff and vertical landing (STOVL) aircraft applications.īuilt in 1968, the test section of the 9×15 is 9 ft high by 15 ft wide and 33 ft long. Offering state-of-the-art acoustic capabilities, the facility is a vital part of the nation’s aeronautics research plans. With the ever-increasing demand for reducing aircraft noise, the importance of the 9×15 is greater than ever. The 9×15 is a significant asset to the nation and the aero-propulsion community because of its unique ability to test large-scale hardware in a continuous subsonic air stream. Facility Overview Advanced Ducted Propulsor (ADP) Fan Commissioning Test (side view) in the 9- by 15-Foot Low-Speed Wind Tunnel (9×15) It is the only national facility that can simulate takeoff, approach, and landing in a continuous subsonic environment. The 9- by 15-Foot Low-Speed Wind Tunnel (9×15) is the most utilized low-speed propulsion acoustic facility in the world. Based on this modified simulation the alternate attachment point does not appear to offer a significant increase in allowable roll rate over the nominal configuration.Home > Facilities 9×15 Low-Speed Wind Tunnel Reevaluating the impact of the alternate attachment points using a simulation modified to account for these results showed significantly reduced roll rate attenuation tendencies when compared to the original simulation. ![]() ![]() Comparisons for the alternate attachment location indicate that riser twist plays a significant role in determining roll rate attenuation characteristics. Comparison of the experimental data to a Program To Optimize Simulated Trajectories (POST II) simulation of the experiment yielded results for the nominal attachment point that indicate differences between the low-speed pitch and yaw damping derivatives in the aerodynamic database and the physical model. Experimental results indicated that the alternate attachment location showed a somewhat greater tendency to attenuate initial roll rate and reduce roll rate oscillations than the nominal location. Two attachment locations were tested: the current design nominal and an alternate. The primary test objective was to assess the ability of the Orion Crew Module drogue parachute system to adequately stabilize the CM and reduce angular rates at low subsonic Mach numbers. Low-Speed Flight Dynamic Tests and Analysis of the Orion Crew Module Drogue Parachute System A test of a dynamically scaled model of the NASA Orion Crew Module (CM) with drogue parachutes was conducted in the NASA-Langley 20-Foot Vertical Spin Tunnel.
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |