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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Page 1
... studies of large helicopter mod- els , jets , and V / STOL aircraft models in simulated flight . Model scale studies would be necessary to optimize the aerodynamic and acoustic performance of any of the designs . In all designs studied ...
... studies of large helicopter mod- els , jets , and V / STOL aircraft models in simulated flight . Model scale studies would be necessary to optimize the aerodynamic and acoustic performance of any of the designs . In all designs studied ...
Page 11
... studies . If the porous- walls could be protected from downwash and jet blast from V / STOL models , it might be possible to leave the insert in the 80x120 for aerodynamic tests , and only remove it for studies of models sized for the ...
... studies . If the porous- walls could be protected from downwash and jet blast from V / STOL models , it might be possible to leave the insert in the 80x120 for aerodynamic tests , and only remove it for studies of models sized for the ...
Page 15
... studies ( refs . 44-46 ) , and the model wind tunnel is existing . The scale models would be necessary for the following studies of the chosen design concept : 1. Measure the separated flow regions downstream of the insert diffuser and ...
... studies ( refs . 44-46 ) , and the model wind tunnel is existing . The scale models would be necessary for the following studies of the chosen design concept : 1. Measure the separated flow regions downstream of the insert diffuser and ...
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Common terms and phrases
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