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 3
... speeds . They are all low - speed facilities . The DNW Wind Tunnel has a top speed of 150 knots , the highest speed of the group . Mort et al . ( ref . 7 ) suggested that a large - scale wind tunnel speed of 300 knots would satisfy most ...
... speeds . They are all low - speed facilities . The DNW Wind Tunnel has a top speed of 150 knots , the highest speed of the group . Mort et al . ( ref . 7 ) suggested that a large - scale wind tunnel speed of 300 knots would satisfy most ...
Page 7
... speed ( Compilation of Cali- bration Data of the German - Dutch Wind Tunnel , MP - 82.01 , March 13 , 1982 , by the staff of DNW ) and is similar to the coefficient given in reference 21. The wind- tunnel speed is limited by either maximum ...
... speed ( Compilation of Cali- bration Data of the German - Dutch Wind Tunnel , MP - 82.01 , March 13 , 1982 , by the staff of DNW ) and is similar to the coefficient given in reference 21. The wind- tunnel speed is limited by either maximum ...
Page 11
... maximum test section speed of a 40x80 test section with porous wall is estimated to be 209 knots , whereas the top speed with the 30x60 open jet was estimated to be 197 knots ( fig . 12 ) . The acoustic vane loss was included . A 40x80 ...
... maximum test section speed of a 40x80 test section with porous wall is estimated to be 209 knots , whereas the top speed with the 30x60 open jet was estimated to be 197 knots ( fig . 12 ) . The acoustic vane loss was included . A 40x80 ...
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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