Large-scale Aeroacoustic Research Feasibility and Conceptual Design of Test-section Inserts for the Ames 80- by 120-foot Wind TunnelNational Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990 - Airplanes - 45 pages |
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120-Foot Wind Tunnel 80-Foot Wind absorbed acoustic energy acoustic measurements acoustic vane rows acoustic vane set acoustic wedges acoustically transparent walls acoustically treated aeroacoustic aerodynamic and acoustic AIAA Paper airflow Ames Research Center anechoic approximately attenuation background noise closed jet closed test section closed-jet diameter diffuser drive fans enhanced wall lining existing facility fan drive far-field flow noise flow separation foam frequency geometry helicopter hydraulic diameter Idelchik Kinetic energy knots airspeed Langley 14 loss factor maximum airspeed microphones mineral wool Moffett Field NASA NASA Langley Noiseux nozzle open-jet designs open-jet insert open-jet shear layer open-jet test section open-jet wind tunnels PLAN VIEW polyurethane porous layer porous wall pressure loss reflections refraction rotor SET 3 CLOSED shown in figure Soderman stator streamwise strut studies test hall Test section speed test-section tion top speed Transonic turbulence turntable unsteady upstream V/STOL velocity wall angle