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Author : James Thomas Crippen
Publisher :
ISBN 13 :
Total Pages : 230 pages
Book Rating : 4.:/5 (773 download)
Download or read book Acoustic Characterization of the NASA Langley 14 X 22 Ft Subsonic Wind Tunnel written by James Thomas Crippen and published by . This book was released on 2011 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Garl L. Gentry
Publisher :
ISBN 13 :
Total Pages : 76 pages
Book Rating : 4.:/5 (317 download)
Download or read book The Langley 14- by 22-foot Subsonic Tunnel written by Garl L. Gentry and published by . This book was released on 1990 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 92 pages
Book Rating : 4.:/5 (317 download)
Download or read book Acoustical Characteristics of the NASA Langley Full Scale Wind Tunnel Test Section written by and published by . This book was released on 1975 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781720634270
Total Pages : 32 pages
Book Rating : 4.6/5 (342 download)
Download or read book NASA Langley Low Speed Aeroacoustic Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-03 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.Booth, Earl R., Jr. and Henderson, Brenda S.Langley Research CenterAEROACOUSTICS; LOW SPEED WIND TUNNELS; WIND TUNNEL TESTS; JET AIRCRAFT NOISE; NASA PROGRAMS; BACKGROUND NOISE; TEST FACILITIES; NOISE INTENSITY; NOISE REDUCTION; FLOW CHARACTERISTICS; MICROPHONES; DATA PROCESSING; ACOUSTIC MEASUREMENT; JET FLOW
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781720604181
Total Pages : 66 pages
Book Rating : 4.6/5 (41 download)
Download or read book Investigation of a Technique for Measuring Dynamic Ground Effect in a Subsonic Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: To better understand the ground effect encountered by slender wing supersonic transport aircraft, a test was conducted at NASA Langley Research Center's 14 x 22 foot Subsonic Wind Tunnel in October, 1997. Emphasis was placed on improving the accuracy of the ground effect data by using a "dynamic" technique in which the model's vertical motion was varied automatically during wind-on testing. This report describes and evaluates different aspects of the dynamic method utilized for obtaining ground effect data in this test. The method for acquiring and processing time data from a dynamic ground effect wind tunnel test is outlined with details of the overall data acquisition system and software used for the data analysis. The removal of inertial loads due to sting motion and the support dynamics in the balance force and moment data measurements of the aerodynamic forces on the model is described. An evaluation of the results identifies problem areas providing recommendations for future experiments. Test results are validated by comparing test data for an elliptical wing planform with an Elliptical wing planform section with a NACA 0012 airfoil to results found in current literature. Major aerodynamic forces acting on the model in terms of lift curves for determining ground effect are presented. Comparisons of flight and wind tunnel data for the TU-144 are presented.Graves, Sharon S.Langley Research CenterGROUND EFFECT (AERODYNAMICS); AERODYNAMIC FORCES; SUBSONIC WIND TUNNELS; WIND TUNNEL TESTS; DATA ACQUISITION; AIRCRAFT DESIGN; AERODYNAMIC CONFIGURATIONS; AIRCRAFT CONFIGURATIONS; SLENDER WINGS; WING PLANFORMS; SUPERSONIC TRANSPORTS; TU-144 AIRCRAFT; VERTICAL MOTION
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781720372608
Total Pages : 46 pages
Book Rating : 4.3/5 (726 download)
Download or read book Aeroacoustic Experiments in the NASA Langley Low-Turbulence Pressure Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-29 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: A phased microphone array was used in the NASA Langley Low-Turbulence Pressure Tunnel to obtain acoustic data radiating from high-lift wing configurations. The data included noise localization plots and acoustic spectra. The tests were performed at Reynolds numbers based on the cruise-wing chord, ranging from 3.6 x 10(exp 6) to 19.2 x 10(exp 6). The effects of Reynolds number were small and monotonic for Reynolds numbers above 7.2 x 10(exp 6).Choudhari, Meelan M. and Lockard, David P. and Macaraeg, Michele G. and Singer, Bart A. and Streett, Craig L. and Neubert, Guy R. and Stoker, Robert W. and Underbrink, James R. and Berkman, Mert E. and Khorrami, Mehdi R.Langley Research CenterAEROACOUSTICS; LOW TURBULENCE; WIND TUNNEL TESTS; ACOUSTIC PROPERTIES; PRESSURE GRADIENTS; REYNOLDS NUMBER; WING FLAPS; BOUNDARY LAYER THICKNESS; VORTICES; AIRCRAFT NOISE; PHASED ARRAYS; PRESSURE DISTRIBUTION
Author : Nasa Technical Reports Server (Ntrs)
Publisher : BiblioGov
ISBN 13 : 9781289247324
Total Pages : 34 pages
Book Rating : 4.2/5 (473 download)
Download or read book Nasa Langley Low Speed Aeroacoustic Wind Tunnel written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 : Paul T. Soderman
Publisher :
ISBN 13 :
Total Pages : 56 pages
Book Rating : 4.:/5 (317 download)
Download or read book Large-scale Aeroacoustic Research Feasibility and Conceptual Design of Test-section Inserts for the Ames 80- by 120-foot Wind Tunnel written by Paul T. Soderman and published by . This book was released on 1990 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Milo D. Dahl
Publisher :
ISBN 13 :
Total Pages : 32 pages
Book Rating : 4.:/5 (31 download)
Download or read book Comparison Between Design and Installed Acoustic Characteristics of NASA Lewis 9- by 15-Foot Low-Speed Wind Tunnel Acoustic Treatment written by Milo D. Dahl and published by . This book was released on 1990 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 194 pages
Book Rating : 4.:/5 (317 download)
Download or read book Forward Velocity Effects on Fan Noise and the Suppression Characteristics of Advanced Inlets as Measured in the NASA Ames 40 by 80 Foot Wind Tunnel: Acoustic Data Report written by and published by . This book was released on 1981 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721779383
Total Pages : 36 pages
Book Rating : 4.7/5 (793 download)
Download or read book Model-Scale Aerodynamic Performance Testing of Proposed Modifications to the NASA Langley Low Speed Aeroacoustic Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-24 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 : John F. Wilby
Publisher :
ISBN 13 :
Total Pages : 94 pages
Book Rating : 4.:/5 (317 download)
Download or read book An Analysis of Sound Absorbing Linings for the Interior of the NASA Ames 80 X 120-foot Wind Tunnel written by John F. Wilby and published by . This book was released on 1985 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781719500500
Total Pages : 80 pages
Book Rating : 4.5/5 (5 download)
Download or read book Acoustic Performance of the Geae Ups Research Fan in the NASA Glenn 9- By 15-Foot Low-Speed Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-22 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: A model advanced turbofan was acoustically tested in the NASA Glenn 9- by 15-Foot Low-Speed Wind Tunnel in 1994. The Universal Propulsion Simulator fan was designed and manufactured by General Electric Aircraft Engines, and included an active core, as well as bypass, flow paths. The fan was tested with several rotors featuring unswept, forward-swept and aft-swept designs of both metal and composite construction. Sideline acoustic data were taken with both hard and acoustically treated walls in the flow passages. The fan was tested within an airflow at a Mach number of 0.20, which is representative of aircraft takeoff/approach conditions. All rotors showed similar aerodynamic performance. However, the composite rotors typically showed higher noise levels than did corresponding metal rotors. Aft and forward rotor sweep showed at most modest reductions of transonic multiple pure tone levels. However, rotor sweep often introduced increased rotor-stator interaction tone levels. Broadband noise was typically higher for the composite rotors and also for the aft-swept metal rotor. Transonic MPT generation was reduced with increasing fan axis angle of attack (AOA); however, higher downstream noise levels did increase with AOA resulting in higher overall Effective Perceived Noise Level. Woodward, Richard P. and Hughes, Christopher E. Glenn Research Center ACOUSTIC PROPERTIES; NOISE INTENSITY; AERODYNAMIC CHARACTERISTICS; MACH NUMBER; ANGLE OF ATTACK; AIR FLOW; WIND TUNNEL MODELS; WIND TUNNEL TESTS
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722189488
Total Pages : 24 pages
Book Rating : 4.1/5 (894 download)
Download or read book Effect of Collector Configuration on Test Section Turbulence Levels in an Open-Jet Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-02 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flow quality studies in the Langley 14- by 22-Foot Subsonic Tunnel indicated periodic flow pulsation at discrete frequencies in the test section when the tunnel operated in an open-jet configuration. To alleviate this problem, experiments were conducted in a 1/24-scale model of the full-scale tunnel to evaluate the turbulence reduction potential of six collector configurations. As a result of these studies, the original bell-mouth collector of the 14- by 22-Foot Subsonic Tunnel was replaced by a collector with straight walls, and a slot was incorporated between the trailing edge of the collector and the entrance of the diffuser. Manuel, G. S. and Molloy, John K. and Barna, P. Stephen Langley Research Center RTOP 505-61-41-02...
Author : Harvey H. Hubbard
Publisher :
ISBN 13 :
Total Pages : 620 pages
Book Rating : 4.F/5 ( download)
Download or read book Aeroacoustics of Flight Vehicles written by Harvey H. Hubbard and published by . This book was released on 1991 with total page 620 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1989 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 488 pages
Book Rating : 4.:/5 (3 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 488 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
