Large-scale Aeroacoustic Research Feasibility and Conceptual Design of Test-section Inserts for the Ames 80- by 120-foot Wind Tunnel
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40 by 80FOOT OPEN JET FOR 150 knots AIRSPEED
APPENDIX A PRESSURE LOSS EQUATIONS
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120-Foot Wind Tunnel 80-Foot Wind 80x120 test section absorbed acoustic energy acoustic measurements acoustic testing acoustic vane rows acoustic vane set acoustic wedges acoustically transparent walls aeroacoustic aerodynamic and acoustic AIAA Paper airflow Ames Research Center approximately attenuation background noise boundary-layer closed jet closed test section closed-jet diameter diffuser drive fans enhanced wall lining existing facility fan drive far-field flow noise flow separation frequency geometry helicopter hydraulic diameter inlet Kinetic energy knots airspeed Langley 14 loss coefficient 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 streamwise strut studies test hall Test section speed test-section tion top speed Transonic turbulence turntable unsteady upstream V/STOL velocity