Download or read book Static and Wind Tunnel Aero Performance Tests of NASA Ast Separate Flow Nozzle Noise Reduction Configurations written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-27 with total page 304 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of cold flow model tests to determine the static and wind tunnel performance of several NASA AST separate flow nozzle noise reduction configurations. The tests were conducted by Aero Systems Engineering, Inc., for NASA Glenn Research Center. The tests were performed in the Channels 14 and 6 static thrust stands and the Channel 10 transonic wind tunnel at the FluiDyne Aerodynamics Laboratory in Plymouth, Minnesota. Facility checkout tests were made using standard ASME long-radius metering nozzles. These tests demonstrated facility data accuracy at flow conditions similar to the model tests. Channel 14 static tests reported here consisted of 21 ASME nozzle facility checkout tests and 57 static model performance tests (including 22 at no charge). Fan nozzle pressure ratio varied from 1.4 to 2.0, and fan to core total pressure ratio varied from 1.0 to 1.19. Core to fan total temperature ratio was 1.0. Channel 10 wind tunnel tests consisted of 15 tests at Mach number 0.28 and 31 tests at Mach 0.8. The sting was checked out statically in Channel 6 before the wind tunnel tests. In the Channel 6 facility, 12 ASME nozzle data points were taken and 7 model data points were taken. In the wind tunnel, fan nozzle pressure ratio varied from 1.73 to 2.8, and fan to core total pressure ratio varied from 1.0 to 1.19. Core to fan total temperature ratio was 1.0. Test results include thrust coefficients, thrust vector angle, core and fan nozzle discharge coefficients, total pressure and temperature charging station profiles, and boat-tail static pressure distributions in the wind tunnel. Mikkelsen, Kevin L. and McDonald, Timothy J. and Saiyed, Naseem (Technical Monitor) Glenn Research Center NAS3-98021; RTOP 781-30-12...
Download or read book STATIC AND WIND TUNNEL AERO PERFORMANCE TESTS OF NASA AST SEPARATE FLOW NOZZLE NOISE REDUCTION CONFIGURATION FINAL REPORT NASA written by United States. National Aeronautics and Space Administration and published by . This book was released on 2002* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 2002 with total page 836 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Static Aerodynamic Performance Investigation of a Fluid Shield Nozzle written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: In pursuit of an acoustically acceptable, high performance exhaust system capable of meeting Federal Aviation Regulation 36 Stage 3 noise goals for the High Speed Civil Transport application, General Electric Aircraft Engines conducted a design study to incorporate a fluid shield into a 36-chute suppressor exhaust-nozzle system. After a full scale preliminary mechanical design of the resulting fluid shield exhaust system, scale model aerodynamic performance tests and acoustic tests were conducted to establish both aerodynamic performance and acoustic characteristics. Data are presented as thrust coefficients, discharge coefficients, chute-base pressure drags, and plug static pressure distributions.Balan, C. and Askew, J. W.Glenn Research CenterCIVIL AVIATION; EXHAUST NOZZLES; AERODYNAMIC CHARACTERISTICS; AIRCRAFT ENGINES; MECHANICAL ENGINEERING; SHIELDING; FLUID FLOW; STATIC PRESSURE; DATA REDUCTION; THRUST; PLUGS; PRESSURE DISTRIBUTION; NOZZLE FLOW; NOISE REDUCTION
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1979 with total page 1016 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1981 with total page 1372 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Acoustic and Aerothermal Performance Test of the Axisymmetric Coannular Ejector Nozzle Volume 2 Acoustic Performance written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-13 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: Acoustic and propulsion performance testing of a model-scale Axisymmetric Coannular Ejector nozzle was conducted in the Boeing Low-speed Aeroacoustic Facility. This nozzle is a plug nozzle with an ejector design to provide aspiration of about 20% of the engine flow. A variety of mixing enhancers were designed to promote mixing of the engine and the aspirated flows. These included delta tabs, tone-injection rods, and wheeler ramps. This report addresses the acoustic aspects of the testing. The spectral characteristics of the various configurations of the nozzle are examined on a model-scale basis. This includes indentifying particular noise sources contributing to the spectra and the data are projected to full-scale flyover conditions to evaluate the effectiveness of the nozzle, and of the various mixing enhancers, on reducing the Effective Perceived Noise Levels. Herkes, William Glenn Research Center NAS3-25963; RTOP 714-04-50
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.
Download or read book Wind Tunnel Performance Test of Coannular Plug Nozzles written by Paul S. Staid and published by . This book was released on 1978 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High speed Wind Tunnels written by Luigi Crocco and published by . This book was released on 1946 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt: The importance assumed in recent times by experimental supersonic wind tunnels, as well as the power required, has brought about the need for a study which would permit a comparison of the types tested and the principal theoretical plans.
Download or read book Model Scale Aerodynamic Performance Testing of Proposed Modifications to the Nasa Langley Low Speed Aeroacoustic Wind Tunnel written by Earl R. Booth and published by BiblioGov. This book was released on 2013-07 with total page 24 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.
Download or read book Effects of Convoluted Divergent Flap Contouring on the Performance of a Fixed Geometry Nonaxisymmetric Exhaust Nozzle written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-30 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the model preparation area of the Langley 16-Foot Transonic Tunnel to determine the effects of convoluted divergent-flap contouring on the internal performance of a fixed-geometry, nonaxisymmetric, convergent-divergent exhaust nozzle. Testing was conducted at static conditions using a sub-scale nozzle model with one baseline and four convoluted configurations. All tests were conducted with no external flow at nozzle pressure ratios from 1.25 to approximately 9.50. Results indicate that baseline nozzle performance was dominated by unstable, shock-induced, boundary-layer separation at overexpanded conditions. Convoluted configurations were found to significantly reduce, and in some cases totally alleviate separation at overexpanded conditions. This result was attributed to the ability of convoluted contouring to energize and improve the condition of the nozzle boundary layer. Separation alleviation offers potential for installed nozzle aeropropulsive (thrust-minus-drag) performance benefits by reducing drag at forward flight speeds, even though this may reduce nozzle thrust ratio as much as 6.4% at off-design conditions. At on-design conditions, nozzle thrust ratio for the convoluted configurations ranged from 1% to 2.9% below the baseline configuration; this was a result of increased skin friction and oblique shock losses inside the nozzle.Asbury, Scott C. and Hunter, Craig A.Langley Research CenterCONVERGENT-DIVERGENT NOZZLES; BOUNDARY LAYER SEPARATION; WIND TUNNEL NOZZLES; WIND TUNNEL TESTS; NOZZLE FLOW; OBLIQUE SHOCK WAVES; FLOW VISUALIZATION; NOZZLE GEOMETRY; AERODYNAMIC DRAG; SKIN FRICTION; PRESSURE RATIO; FLAPS (CONTROL SURFACES)
Download or read book Static Performance of a Fixed Geometry Exhaust Nozzle Incorporating Porous Cavities for Shock Boundary Layer Interaction Control written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-20 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the model preparation area of the Langley 16-Foot Transonic Tunnel to determine the internal performance of a fixed-geometry exhaust nozzle incorporating porous cavities for shock-boundary layer interaction control. Testing was conducted at static conditions using a sub-scale nozzle model with one baseline and 27 porous configurations. For the porous configurations, the effects of percent open porosity, hole diameter, and cavity depth were determined. All tests were conducted with no external flow at nozzle pressure ratios from 1.25 to approximately 9.50. Results indicate that baseline nozzle performance was dominated by unstable, shock-induced, boundary-layer separation at over-expanded conditions. Porous configurations were capable of controlling off-design separation in the nozzle by either alleviating separation or encouraging stable separation of the exhaust flow. The ability of the porous nozzle concept to alternately alleviate separation or encourage stable separation of exhaust flow through shock-boundary layer interaction control offers tremendous off-design performance benefits for fixed-geometry nozzle installations. In addition, the ability to encourage separation on one divergent flap while alleviating it on the other makes it possible to generate thrust vectoring using a fixed-geometry nozzle. Asbury, Scott C. and Hunter, Craig A. Langley Research Center RTOP 538-14-12-01
Download or read book NASA SP written by and published by . This book was released on 1992 with total page 512 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Task 2 Flow Solution for Advanced Separate Flow Nozzles Response a written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-31 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: NASA Glenn Research Center funded a computational study to investigate the effect of chevrons and tabs on the exhaust plume from separate flow nozzles. Numerical studies were conducted at typical takeoff power with 0.28 M flight speed. Report provides numerical data and insights into the mechanisms responsible for increased mixing.Kenzakowski, D. C. and Shipman, J. and Dash, S. M. and Saiyed, Naseem (Technical Monitor)Glenn Research CenterPLUMES; EXHAUST GASES; ACOUSTIC NOZZLES; STRUCTURED GRIDS (MATHEMATICS); AEROACOUSTICS; AIRCRAFT NOISE; MIXERS; NOISE REDUCTION
