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There are a total of 21 record(s) matching your query.
Sorted by: Date Added To NTRS in Descending order
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Effects of blade-vane ratio and rotor-stator spacing of fan noise with forward velocity
Author(s): Woodward, R. P.; Glaser, F. W.
Abstract: A research fan stage was acoustically tested in an anechoic wind tunnel with a 41 m/sec tunnel flow. Two stator vane numbers giving cut-on and cut-off conditions were tested at three rotor-stator spacings ranging from about ...
NASA Center: Glenn Research Center
Publication Year: 1981
Added to NTRS: 2004-11-03
Accession Number: 81N31956; Document ID: 19810023413; Report Number: E-971, NASA-TM-82690
Low flight speed acoustic results for a supersonic inlet with auxiliary inlet doors
Author(s): Woodward, R. P.; Glaser, F. W.; Lucas, J. G.
Abstract: A model supersonic inlet with auxiliary inlet doors and bounday layer bleeds was acoustically tested in simulated low speed flight up to Mach 0.2 in the NASA Lewis 9x15 Anechoic Wind Tunnel and statically in the NASA Lewis ...
NASA Center: Glenn Research Center
Publication Year: 1982
Added to NTRS: 2004-11-03
Accession Number: 83N27794; Document ID: 19830019523; Report Number: E-1694, NAS 1.15:83411, NASA-TM-83411
Effects of blade-vane ratio and rotor-stator spacing on fan noise with forward velocity
Author(s): Woodward, R. P.; Glaser, F. W.
Abstract: A research fan stage is acoustically tested in an anechoic wind tunnel with a 41 m/sec tunnel flow. Two stator vane numbers giving cut-on and cut-off conditions are tested at three rotor stator spacings ranging from 0.5 to ...
NASA Center: Glenn Research Center
Publication Year: 1981
Added to NTRS: 2004-11-03
Accession Number: 81A48628; Document ID: 19810064224; Report Number: AIAA PAPER 81-2032
Acoustic properties of a supersonic fan
Author(s): Goldstein, A. W.; Glaser, F. W.; Coats, J. W.
Abstract: Tests of supersonic rotors designed to reduce forward propagating pressure waves and the accompanying blade passing tones and multiple pure tones showed the wave propagation and noise reduction to have been obtained at the ...
NASA Center: Glenn Research Center
Publication Year: 1973
Added to NTRS: 2004-11-03
Accession Number: 73N15025; Document ID: 19730006298; Report Number: E-6953, NASA-TN-D-7096
Acoustic and aerodynamic effects of rotor pitch angles for a variable pitch, 6 foot diameter fan stage
Author(s): Woodward, R. P.; Glaser, F. W.
Abstract: An externally driven, 1.2 pressure ratio full-scale fan stage with an adjustable pitch rotor was tested in an outdoor facility at the Lewis Research Center. Rotor pitch angles resulting in minimum sideline perceived noise ...
NASA Center: Glenn Research Center
Publication Year: 1976
Added to NTRS: 2004-11-03
Accession Number: 76N26155; Document ID: 19760019067; Report Number: E-8753, NASA-TM-X-73418
Mean rotor wake characteristics of an aerodynamically loaded 0.5 m diameter fan
Author(s): Shaw, L. M.; Glaser, F. W.
Abstract: Mean rotor wake properties at several downstream distances behind the rotor of a loaded 1.2 pressure ratio fan were measured with a cross film anemometer in an anechoic wind tunnel. Mean wake characteristics in the midspan ...
NASA Center: Glenn Research Center
Publication Year: 1981
Added to NTRS: 2004-11-03
Accession Number: 81N16053; Document ID: 19810007538; Report Number: E-674, NASA-TM-81657
Effect of inflow control on inlet noise of a cut-on fan
Author(s): Woodward, R. P.; Glaser, F. W.
Abstract: A cut-on, high tip speed fan stage was acoustically tested with three configurations of an inflow control device in the NASA Lewis anechoic chamber. Although this was a cut-on design, rotor-inflow interaction appeared to be ...
NASA Center: Glenn Research Center
Publication Year: 1980
Added to NTRS: 2004-11-03
Accession Number: 80A35993; Document ID: 19800051823; Report Number: AIAA PAPER 80-1049
Acoustic and aerodynamic effects of rotor pitch angle for a variable-pitch, 6-foot diameter fan stage
Author(s): Woodward, R. P.; Glaser, F. W.
Abstract: An externally driven, 1.2 pressure ratio full-scale fan stage with an adjustable pitch rotor was tested in an outdoor facility at the Lewis Research Center. Rotor pitch angles resulting in minimum sideline perceived noise ...
NASA Center: Glenn Research Center
Publication Year: 1976
Added to NTRS: 2004-11-03
Accession Number: 76A38086; Document ID: 19760055120; Report Number: AIAA PAPER 76-573
Mean rotor wake characteristics of an aerodynamically loaded 0.5 m diameter fan
Author(s): Shaw, L. M.; Glaser, F. W.
Abstract: Mean rotor wake properties at several downstream distances behind the rotor of a loaded 1.2 pressure ratio fan were measured with a cross film anemometer in an anechoic wind tunnel. Mean wake characteristics in the midspan ...
NASA Center: Glenn Research Center
Publication Year: 1981
Added to NTRS: 2004-11-03
Accession Number: 81A20830; Document ID: 19810036426; Report Number: AIAA PAPER 81-0208
Low flight speed acoustic results for a supersonic inlet with auxiliary inlet doors
Author(s): Woodward, R. P.; Glaser, F. W.; Lucas, J. G.
Abstract: A model supersonic inlet with auxiliary inlet doors and boundary layer bleeds was acoustically tested in simulated low speed flight up to Mach 0.2 in the NASA Lewis 9 x 15 Anechoic Wind Tunnel and statically in the NASA ...
NASA Center: Glenn Research Center
Publication Year: 1983
Added to NTRS: 2004-11-03
Accession Number: 83A45517; Document ID: 19830064299; Report Number: AIAA PAPER 83-1415
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