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Modification And Additional High Speed Testing In The Nasa Langley 16 Foot Transonic Wind Tunnel Of The Adam Model Developed Under Af33615 3293 Knuckle Interference Testing
Download Modification And Additional High Speed Testing In The Nasa Langley 16 Foot Transonic Wind Tunnel Of The Adam Model Developed Under Af33615 3293 Knuckle Interference Testing full books in PDF, epub, and Kindle. Read online Modification And Additional High Speed Testing In The Nasa Langley 16 Foot Transonic Wind Tunnel Of The Adam Model Developed Under Af33615 3293 Knuckle Interference Testing ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Wind Tunnel and Propulsion Test Facilities by : Philip S. Antón
Download or read book Wind Tunnel and Propulsion Test Facilities written by Philip S. Antón and published by Minnesota Historical Society. This book was released on 2004 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: The National Aeronautics and Space Administration's (NASA's) wind tunnel and propulsion test facilities continue to be important to U.S. competitiveness across the military, commercial, and space sectors. Unfortunately, management issues are creating real risks to these facilities. This technical report supports a companion monograph (Wind Tunnel and Propulsion Test Facilities: An Assessment of NASA's Capabilities to Serve National Needs, MG-178-NASA/OSD), providing more detailed data, observations, and conclusions about the future of NASA's wind tunnel and propulsion test facilities.
Book Synopsis Wind Tunnel Test Techniques by : Colin Britcher
Download or read book Wind Tunnel Test Techniques written by Colin Britcher and published by Academic Press. This book was released on 2023-10-20 with total page 672 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind Tunnel Test Techniques: Design and Use at Low and High Speeds with Statistical Engineering Applications provides an up-to-date treatment of the topic. Beginning with a brief history of wind tunnels and its types and uses, the book goes on to cover subsonic, supersonic and hypersonic wind tunnel design and construction, calibration, boundary corrections, flow quality assessment, pressure surveys, and dynamic testing. It also focuses on wind tunnel facilities, making it useful for both the designer and operator. Engineers and graduate students in aerospace, automotive and similar programs will find this book useful in their work with experimental aerodynamics, gas dynamics, facility design and performance. - Deals with a broad range of flow speeds in wind tunnels, from low speed to high speed - Provides a discussion of similarity laws as well as material on statistical analysis - Includes coverage on facility-to-facility and facility-to-CFD correlation - Presents advanced topics such as cryogenic wind tunnels, ground simulation in automotive testing, and propulsion testing
Book Synopsis Flow-visualization Techniques Used at High Speed by Configuration Aerodynamics Wind-tunnel-test Team by : John E. Lamar
Download or read book Flow-visualization Techniques Used at High Speed by Configuration Aerodynamics Wind-tunnel-test Team written by John E. Lamar and published by . This book was released on 2001 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper summarizes a variety of optically based flow-visualization techniques used for high-speed research by the Configuration Aerodynamics Wind-Tunnel-Test Team of the High-Speed Research Program during its tenure. The work of other national experts is included for completeness. Details of each technique with applications and status in various national wind tunnels are given.
Book Synopsis Apollo Wind Tunnel Testing Program by : William C. Moseley (Jr.)
Download or read book Apollo Wind Tunnel Testing Program written by William C. Moseley (Jr.) and published by . This book was released on 1966 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Space shuttle wind tunnel testing program summary by : A. M. Whitnah
Download or read book Space shuttle wind tunnel testing program summary written by A. M. Whitnah and published by . This book was released on 1984 with total page 536 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720479949 Total Pages :64 pages Book Rating :4.4/5 (799 download)
Book Synopsis Direct Validation of the Wall Interference Correction System of the Ames 11-Foot Transonic Wind Tunnel by : National Aeronautics and Space Administration (NASA)
Download or read book Direct Validation of the Wall Interference Correction System of the Ames 11-Foot Transonic Wind Tunnel 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 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Data from the test of a large semispan model was used to perform a direct validation of a wall interference correction system for a transonic slotted wall wind tunnel. At first, different sets of uncorrected aerodynamic coefficients were generated by physically changing the boundary condition of the test section walls. Then, wall interference corrections were computed and applied to all data points. Finally, an interpolation of the corrected aerodynamic coefficients was performed. This interpolation made sure that the corrected Mach number of a given run would be constant. Overall, the agreement between corresponding interpolated lift, drag, and pitching moment coefficient sets was very good. Buoyancy corrections were also investigated. These studies showed that the accuracy goal of one drag count may only be achieved if reliable estimates of the wall interference induced buoyancy correction are available during a test.Ulbrich, Norbert and Boone, Alan R.Ames Research CenterCORRECTION; TRANSONIC WIND TUNNELS; WALL FLOW; WIND TUNNEL TESTS; AERODYNAMIC INTERFERENCE; SLOTTED WIND TUNNELS; INTERPOLATION; MACH NUMBER; PITCHING MOMENTS; LIFT; BOUNDARY CONDITIONS; ACCURACY; BUOYANCY
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)
Book Synopsis 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 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
Book Synopsis Measurement of the Pressure Fluctuations in the Test Section of the 1-foot Transonic Tunnel in the Frequency Range from 5 to 1250 Cps by : J. E. Robertson
Download or read book Measurement of the Pressure Fluctuations in the Test Section of the 1-foot Transonic Tunnel in the Frequency Range from 5 to 1250 Cps written by J. E. Robertson and published by . This book was released on 1962 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781724695772 Total Pages :436 pages Book Rating :4.6/5 (957 download)
Book Synopsis Transonic Wind Tunnel Test of a 14 Percent Thick Oblique Wing by : National Aeronautics and Space Administration (NASA)
Download or read book Transonic Wind Tunnel Test of a 14 Percent Thick Oblique Wing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-04 with total page 436 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted at the ARC 11- by 11-Foot Transonic Wind Tunnel as part of the Oblique Wing Research Aircraft Program to study the aerodynamic performance and stability characteristics of a 0.087-scale model of an F-8 airplane fitted with an oblique wing designed by Rockwell International. The 10.3 aspect ratio, straight-tapered wing of 0.14 thickness/chord ratio was tested at two different mounting heights above the fuselage. Additional tests were conducted to assess low-speed behavior with and without flaps, aileron effectiveness at representative flight conditions, and transonic drag divergence with 0 degree wing sweep. Longitudinal stability data were obtained at sweep angles of 0, 30, 45, 60, and 65 degrees, at Mach numbers ranging from 0.25 to 1.40. Test Reynolds numbers varied from 3.2 to 6.6 x 10 exp 6/ft. and angle of attack ranged from -5 to +18 degrees. Most data were taken at zero sideslip, but a few runs were at sideslip angles of +/- 5 degrees. The raised wing position proved detrimental overall, although side force and yawing moment were reduced at some conditions. Maximum lift coefficient with the flaps deflected was found to fall short of the value predicted in the preliminary design document. The performance and trim characteristics of the present wing are generally inferior to those obtained for a previously tested wing designed at ARC. Kennelly, Robert A., Jr. and Kroo, Ilan M. and Strong, James M. and Carmichael, Ralph L. Ames Research Center NASA-TM-102230, A-89236, NAS 1.15:102230 RTOP 533-06-01...
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722867805 Total Pages :78 pages Book Rating :4.8/5 (678 download)
Book Synopsis Wall Interference and Boundary Simulation in a Transonic Wind Tunnel with a Discretely Slotted Test Section by : National Aeronautics and Space Administration (NASA)
Download or read book Wall Interference and Boundary Simulation in a Transonic Wind Tunnel with a Discretely Slotted Test Section written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational simulation of a transonic wind tunnel test section with longitudinally slotted walls is developed and described herein. The nonlinear slot model includes dynamic pressure effects and a plenum pressure constraint, and each slot is treated individually. The solution is performed using a finite-difference method that solves an extended transonic small disturbance equation. The walls serve as the outer boundary conditions in the relaxation technique, and an interaction procedure is used at the slotted walls. Measured boundary pressures are not required to establish the wall conditions but are currently used to assess the accuracy of the simulation. This method can also calculate a free-air solution as well as solutions that employ the classical homogeneous wall conditions. The simulation is used to examine two commercial transport aircraft models at a supercritical Mach number for zero-lift and cruise conditions. Good agreement between measured and calculated wall pressures is obtained for the model geometries and flow conditions examined herein. Some localized disagreement is noted, which is attributed to improper simulation of viscous effects in the slots. Al-Saadi, Jassim A. Langley Research Center...
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722411008 Total Pages :62 pages Book Rating :4.4/5 (11 download)
Book Synopsis Further Buffeting Tests in a Cryogenic Wind Tunnel by : National Aeronautics and Space Administration (NASA)
Download or read book Further Buffeting Tests in a Cryogenic Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-08 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: Further measurements of buffeting, using wing-root strain gauges, were made in the NASA Langley 0.3 m Cryogenic Wind Tunnel to refine techniques which will be used in larger cryogenic facilities such as the United States National Transonic Facility (NTF) and European Transonic Wind Tunnel (ETW). The questions addressed included the relative importance of variations in frequency parameter and Reynolds number, the choice of model material (considering both stiffness and damping) and the effects of static aeroelastic distortion. The main series of tests was made on half models of slender 65 deg delta wings with a sharp leading edge. The three delta wings had the same planform but widely different bending stiffness and frequencies (obtained by varying both the material and the thickness of the wings). It was known that the flow on this configuration would be insensitive to variations in Reynold number. Additional tests were made on one unswept half-wing of aspect ratio 1.5 with an NPL 9510 aerofoil section, known to be sensitive to variations in Reynolds number at transonic speeds. For brevity the test Mach numbers were restricted to M = 0.21 and 0.35 for the delta wings and to M = 0.30 for the unswept wing. Mabey, D. G. and Boyden, R. P. and Johnson, W. G., Jr. Langley Research Center...
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722242046 Total Pages :60 pages Book Rating :4.2/5 (42 download)
Book Synopsis Application of Rapid Prototyping Methods to High-Speed Wind Tunnel Testing by : National Aeronautics and Space Administration (NASA)
Download or read book Application of Rapid Prototyping Methods to High-Speed Wind Tunnel Testing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-08 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study was undertaken in MSFC's 14-Inch Trisonic Wind Tunnel to determine if rapid prototyping methods could be used in the design and manufacturing of high speed wind tunnel models in direct testing applications, and if these methods would reduce model design/fabrication time and cost while providing models of high enough fidelity to provide adequate aerodynamic data, and of sufficient strength to survive the test environment. Rapid prototyping methods utilized to construct wind tunnel models in a wing-body-tail configuration were: fused deposition method using both ABS plastic and PEEK as building materials, stereolithography using the photopolymer SL-5170, selective laser sintering using glass reinforced nylon, and laminated object manufacturing using plastic reinforced with glass and 'paper'. This study revealed good agreement between the SLA model, the metal model with an FDM-ABS nose, an SLA nose, and the metal model for most operating conditions, while the FDM-ABS data diverged at higher loading conditions. Data from the initial SLS model showed poor agreement due to problems in post-processing, resulting in a different configuration. A second SLS model was tested and showed relatively good agreement. It can be concluded that rapid prototyping models show promise in preliminary aerodynamic development studies at subsonic, transonic, and supersonic speeds. Springer, A. M. Marshall Space Flight Center...
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722337162 Total Pages :58 pages Book Rating :4.3/5 (371 download)
Book Synopsis Description and Evaluation of an Interference Assessment for a Slotted-Wall Wind Tunnel by : National Aeronautics and Space Administration (NASA)
Download or read book Description and Evaluation of an Interference Assessment for a Slotted-Wall Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel interference assessment method applicable to test sections with discrete finite-length wall slots is described. The method is based on high order panel method technology and uses mixed boundary conditions to satisfy both the tunnel geometry and wall pressure distributions measured in the slotted-wall region. Both the test model and its sting support system are represented by distributed singularities. The method yields interference corrections to the model test data as well as surveys through the interference field at arbitrary locations. These results include the equivalent of tunnel Mach calibration, longitudinal pressure gradient, tunnel flow angularity, wall interference, and an inviscid form of sting interference. Alternative results which omit the direct contribution of the sting are also produced. The method was applied to the National Transonic Facility at NASA Langley Research Center for both tunnel calibration tests and tests of two models of subsonic transport configurations. Kemp, William B., Jr. Unspecified Center...
Book Synopsis Support Interference of Wind Tunnel Models by : Marie H. Tuttle
Download or read book Support Interference of Wind Tunnel Models written by Marie H. Tuttle and published by . This book was released on 1981 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-Speed Wind Tunnel Testing by : Alan Pope
Download or read book Low-Speed Wind Tunnel Testing written by Alan Pope and published by Wiley-Interscience. This book was released on 1984 with total page 562 pages. Available in PDF, EPUB and Kindle. Book excerpt: Good,No Highlights,No Markup,all pages are intact, Slight Shelfwear,may have the corners slightly dented, may have slight color changes/slightly damaged spine.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781723487941 Total Pages :170 pages Book Rating :4.4/5 (879 download)
Book Synopsis Wind Tunnel Investigation of Vortex Flows on F/a-18 Configuration at Subsonic Through Transonic Speed by : National Aeronautics and Space Administration (NASA)
Download or read book Wind Tunnel Investigation of Vortex Flows on F/a-18 Configuration at Subsonic Through Transonic Speed written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-23 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel experiment was conducted in the David Taylor Research Center 7- by 10-Foot Transonic Tunnel of the wing leading-edge extension (LEX) and forebody vortex flows at subsonic and transonic speeds about a 0.06-scale model of the F/A-18. The primary goal was to improve the understanding and control of the vortical flows, including the phenomena of vortex breakdown and vortex interactions with the vertical tails. Laser vapor screen flow visualizations, LEX, and forebody surface static pressures, and six-component forces and moments were obtained at angles of attack of 10 to 50 degrees, free-stream Mach numbers of 0.20 to 0.90, and Reynolds numbers based on the wing mean aerodynamic chord of 0.96 x 10(exp 6) to 1.75 x 10(exp 6). The wind tunnel results were correlated with in-flight flow visualizations and handling qualities trends obtained by NASA using an F-18 High-Alpha Research Vehicle (HARV) and by the Navy and McDonnell Douglas on F-18 aircraft with LEX fences added to improve the vertical tail buffet environment. Key issues that were addressed include the sensitivity of the vortical flows to the Reynolds number and Mach number; the reduced vertical tail excitation, and the corresponding flow mechanism, in the presence of the LEX fence; the repeatability of data obtained during high angle-of-attack wind tunnel testing of F-18 models; the effects of particle seeding for flow visualization on the quantitative model measurements; and the interpretation of off-body flow visualizations obtained using different illumination and particle seeding techniques. Erickson, Gary E. Glenn Research Center F-18 AIRCRAFT; FOREBODIES; INTERACTIONAL AERODYNAMICS; LEADING EDGES; VORTEX BREAKDOWN; VORTICES; WIND TUNNEL TESTS; WINGS; ANGLE OF ATTACK; BUFFETING; FLOW VISUALIZATION; MACH NUMBER; REYNOLDS NUMBER; STABILIZERS (FLUID DYNAMICS); SUBSONIC SPEED; TAIL ASSEMBLIES; TRANSONIC SPEED; TRANSONIC WIND TUNNELS...
