Model-Scale Aerodynamic Performance Testing of Proposed Modifications to the NASA Langley Low Speed Aeroacoustic Wind Tunnel PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Model-Scale Aerodynamic Performance Testing of Proposed Modifications to the NASA Langley Low Speed Aeroacoustic Wind Tunnel PDF full book. Access full book title Model-Scale Aerodynamic Performance Testing of Proposed Modifications to the NASA Langley Low Speed Aeroacoustic Wind Tunnel by National Aeronautics and Space Administration (NASA). Download full books in PDF and EPUB format.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721779383
Category :
Languages : en
Pages : 36
Get Book Here
Book Description
Tests were performed on a 1/20th-scale model of the Low Speed Aeroacoustic Wind Tunnel to determine the performance effects of insertion of acoustic baffles in the tunnel inlet, replacement of the existing collector with a new collector design in the open jet test section, and addition of flow splitters to the acoustic baffle section downstream of the test section. As expected, the inlet baffles caused a reduction in facility performance. About half of the performance loss was recovered by addition the flow splitters to the downstream baffles. All collectors tested reduced facility performance. However, test chamber recirculation flow was reduced by the new collector designs and shielding of some of the microphones was reduced owing to the smaller size of the new collector. Overall performance loss in the facility is expected to be a 5 percent top flow speed reduction, but the facility will meet OSHA limits for external noise levels and recirculation in the test section will be reduced. Booth, Earl R., Jr. and Coston, Calvin W., Jr. Langley Research Center NASA/TM-2005-213534, L-19093
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721779383
Category :
Languages : en
Pages : 36
Get Book Here
Book Description
Tests were performed on a 1/20th-scale model of the Low Speed Aeroacoustic Wind Tunnel to determine the performance effects of insertion of acoustic baffles in the tunnel inlet, replacement of the existing collector with a new collector design in the open jet test section, and addition of flow splitters to the acoustic baffle section downstream of the test section. As expected, the inlet baffles caused a reduction in facility performance. About half of the performance loss was recovered by addition the flow splitters to the downstream baffles. All collectors tested reduced facility performance. However, test chamber recirculation flow was reduced by the new collector designs and shielding of some of the microphones was reduced owing to the smaller size of the new collector. Overall performance loss in the facility is expected to be a 5 percent top flow speed reduction, but the facility will meet OSHA limits for external noise levels and recirculation in the test section will be reduced. Booth, Earl R., Jr. and Coston, Calvin W., Jr. Langley Research Center NASA/TM-2005-213534, L-19093
Author: Earl R. Booth
Publisher: BiblioGov
ISBN: 9781289265632
Category :
Languages : en
Pages : 24
Get Book Here
Book Description
Tests were performed on a 1/20th-scale model of the Low Speed Aeroacoustic Wind Tunnel to determine the performance effects of insertion of acoustic baffles in the tunnel inlet, replacement of the existing collector with a new collector design in the open jet test section, and addition of flow splitters to the acoustic baffle section downstream of the test section. As expected, the inlet baffles caused a reduction in facility performance. About half of the performance loss was recovered by addition the flow splitters to the downstream baffles. All collectors tested reduced facility performance. However, test chamber recirculation flow was reduced by the new collector designs and shielding of some of the microphones was reduced owing to the smaller size of the new collector. Overall performance loss in the facility is expected to be a 5 percent top flow speed reduction, but the facility will meet OSHA limits for external noise levels and recirculation in the test section will be reduced.
Author: Nasa Technical Reports Server (Ntrs)
Publisher: BiblioGov
ISBN: 9781289247324
Category :
Languages : en
Pages : 34
Get Book Here
Book Description
The NASA Langley Research Center Low Speed Aeroacoustic Wind Tunnel is a premier facility for model-scale testing of jet noise reduction concepts at realistic flow conditions. However, flow inside the open jet test section is less than optimum. A Construction of Facilities project, scheduled for FY 05, will replace the flow collector with a new design intended to reduce recirculation in the open jet test section. The reduction of recirculation will reduce background noise levels measured by a microphone array impinged by the recirculation flow and will improve flow characteristics in the open jet tunnel flow. In order to assess the degree to which this modification is successful, background noise levels and tunnel flow are documented, in order to establish a baseline, in this report.
Author: J. K. Davidson
Publisher:
ISBN:
Category :
Languages : en
Pages : 175
Get Book Here
Book Description
The report presents an analysis of data from a high speed wind tunnel test of a powered propulsive wing aircraft concept; test Mach numbers ranged from 0.4 to 0.96. The model was tested only with undeflected thrust. The prime purpose of the test was to determine the effects of a large pitch range knuckle on the aerodynamic characteristics recorded in a previous test of the same model in the same wind tunnel; a removable, dummy knuckle was used in this test. Secondary purposes of this test were to determine the effects of enlarged fan exit areas, a reshaped flap undersurface and increased fan thrust made possible by the use of a new oil-mist fan bearing lubrication system. Knuckle effects on lift, drag and pitching moments are discussed and documented; both thrust included and thrust removed data are presented. The oil mist lubrication system was found to be an excellent means of lubricating and cooling the fan bearings to provide maximum rpm capability. The reshaped flap undersurface was found to cause a favorable change in the model drag rise characteristics. The momentum coefficient is used to correlate the data; however, the data from this test indicate the need for a better correlation parameter. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 532
Get Book Here
Book Description
Author: Harvey H. Hubbard
Publisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 620
Get Book Here
Book Description
Author: David M. Schuster
Publisher:
ISBN:
Category : Plates (Engineering)
Languages : en
Pages : 44
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 68
Get Book Here
Book Description
Author: William B. Krabill
Publisher:
ISBN:
Category : Aerial photographs in botany
Languages : en
Pages : 776
Get Book Here
Book Description
