Download or read book Development of an Apparatus for Wind Tunnel Dynamic Experiments at High alpha Nasa cr 203760 Jun 23 1997 written by and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development of an Apparatus for Wind Tunnel Dynamic Experiments at High alpha written by Nelson Pedreiro and published by . This book was released on 1997 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development of an Apparatus for Wind Tunnel Dynamic Experiments at High Alpha 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 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: A unique experimental apparatus that allows a wind tunnel model two degrees of freedom has been designed and built. The apparatus was developed to investigate the use of new methods to augment aircraft control in the high angle of attack regime. The model support system provides a platform in which the roll-yaw coupling at high angles of attack can be studied in a controlled environment. Active cancellation of external effects is used to provide a system in which the dynamics are dominated by the aerodynamic loads acting on the wind tunnel model. Pedreiro, Nelson Ames Research Center WIND TUNNEL TESTS; AIRCRAFT CONTROL; AERODYNAMIC LOADS; ACTIVE CONTROL; WIND TUNNEL STABILITY TESTS; AERODYNAMIC STABILITY; WIND TUNNEL APPARATUS; WIND TUNNEL MODELS; DEGREES OF FREEDOM; ANGLE OF ATTACK; FLOW DISTRIBUTION...
Download or read book Evaluation of a Novel Experimental Apparatus for Dynamic Wind Tunnel Testing written by Ihssane Mounir and published by . This book was released on 1997 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Longitudinal Airplane Dynamics Wind Tunnel Test Equipment written by O. B. Tufts and published by . This book was released on 1955 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Wind Tunnel Experiments with the Defense Research Laboratory Apparatus for the Measurement of Longitudinal Dynamic Stability Derivatives at Supersonic Speeds written by R. E. Wilson and published by . This book was released on 1951 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Papers Presented at the Seventh Meeting of the Wind Tunnel and Model Testing Panel written by North Atlantic Treaty Organization. Advisory Group for Aeronautical Research and Development and published by . This book was released on 1955 with total page 1010 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical and Experimental Study of Flow Control Devices for Inlets of Indraft Wind Tunnels 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: The design of closed circuit wind tunnels has historically been performed using rule of thumb which have evolved over the years into a body of useful guidelines. The development of indraft wind tunnels, however, has not been as well documented. The design of indraft wind tunnels is therefore generally performed using a more intuitive approach, often resulting in a facility with disappointing flow quality. The primary problem is a lack of understanding of the flow in the inlet as it passes through the required antiturbulence treatment. For wind tunnels which employ large contraction ratio inlets, this lack of understanding is not serious since the relatively low velocity of the flow through the inlet treatment reduces the sensitivity to improper inlet design. When designing a small contraction ratio inlet, much more careful design is needed in order to reduce the flow distortions generated by the inlet treatment. As part of the National Full Scale Aerodynamics Complex Modification Project, 2-D computational methods were developed which account for the effect of both inlet screens and guide vanes on the test section velocity distribution. Comparisons with experimental data are presented which indicate that the methods accurately compute the flow distortions generated by a screen in a nonuniform velocity field. The use of inlet guide vanes to eliminate the screen induced distortion is also demonstrated both computationally and experimentally. Extensions of the results to 3-D is demonstrated and a successful wind tunnel design is presented. Ross, James C. Ames Research Center...
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...
Download or read book Development of a Quiet Supersonic Wind Tunnel with a Cryogenic Adaptive Nozzle 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 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: Low-disturbance or 'quiet' wind tunnels are now considered an essential part of meaningful boundary layer transition research. Advances in Supersonic Laminar Flow Control (SLFC) technology for swept wings depends on a better understanding of the receptivity of the transition phenomena to attachment-line contamination and cross-flows. This need has provided the impetus for building the Laminar Flow Supersonic Wind Tunnel (LFSWT) at NASA-Ames, as part of the NASA High Speed Research Program (HSRP). The LFSWT was designed to provide NASA with an unequaled capability for transition research at low supersonic Mach numbers (
Download or read book Papers Presented at the Seventh Meeting of the Wind Tunnel and Model Testing Panel written by North Atlantic Treaty Organization. Advisory Group for Aeronautical Research and Development. Wind Tunnel and Model Testing Panel. Meeting and published by . This book was released on 1955 with total page 338 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experiments in a Three Dimensional Adaptive Wall Wind Tunnel 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 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three dimensional adaptive-wall experiments were performed in the Ames Research Center (ARC) 25- by 13-cm indraft wind tunnel. A semispan wing model was mounted to one sidewall of a test section with solid sidewalls, and slotted top and bottom walls. The test section had separate top and bottom plenums which were divided into streamwise and cross-stream compartments. An iterative procedure was demonstrated for measuring wall interference and for adjusting the plenum compartment pressures to eliminate such interference. The experiments were conducted at a freestream Mach number of 0.60 and model angles of attack between 0 and 6 deg. Although in all the experiments wall interference was reduced after the plenum pressures were adjusted, interference could not be completely eliminated. Schairer, E. T. Ames Research Center NASA-TP-2210, A-9255, NAS 1.60:2210 RTOP 505-31-51...
Download or read book Wind Tunnel Testing of the Nasa Dfrc Flutterometer Using a Two Dof Wing Section written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-19 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flutter of an aeroelastic structure is potentially destructive aeroelastic instability. This phenomenon has motivated research within the aeroelastic community to develop methods that can accurately predict aeroelastic instabilities. The Flutterometer method used herein, and as developed by NASA DFRC, is based upon the mu method which has been coupled with wavelet filtering processes in estimating aeroelastic models from flight data. The approach leads to a methodology to predict the occurrence of flutter boundaries, and may prove to reliably predict flutter boundaries during flight tests. An analytical model is used as the first estimate of the aeroelastic structural dynamics, and uncertainty operators are introduced into the system to model variations between the theoretical system and the physical system. The modelling uncertainties are then updated from experimental data. Although the model used did not work well with this particular experiment, a sensitivity analysis was additionally performed and improvements suggested. Strganac, Thomas W. Armstrong Flight Research Center
Download or read book The Modern Design of Experiments for Wind Tunnel Testing written by Richard DeLoach and published by Academic Press. This book was released on 2017-09-01 with total page 608 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Modern Design of Experiments for Wind Tunnel Testing: A Practitioner’s Guide to Formal Experiment Design for Low-Cost, High-Quality Testing in Experimental Aeronautics covers the background theory needed by those unfamiliar with Design of Experiments (DOE) methods, using detailed examples from decades of work at NASA Langley to demonstrate practical realities, applications and limitations. Pioneering NASA research scientist Richard DeLoach shares theoretical background, unrivalled practical experience and detailed examples of a new approach to aeronautical wind tunnel test design. Understanding the needs of wind tunnel practitioners faced with insufficient resources for, and disappointingly unreliable results through, traditional One Factor At a Time (OFAT) testing, DeLoach has spent decades honing his take on the established Design of Experiments (DOE) approach and applying it to aeronautical testing in a wind tunnel setting. His papers on Modern Design of Experiments (MDOE) relating to experimental aeronautics have won him numerous AIAA ‘Outstanding Paper’ and ‘Best Paper’ accolades, as well as a NASA Exceptional Technology Achievement Medal in 2005. In this ground-breaking new book, DeLoach examines the massive potential for cost savings and quality improvement through DOE methods of testing, driving great interest in the topic within the aerospace community. The book is an essential reference to this novel approach from an experienced leader in the field. Offers a true practitioner's guide to this new approach to wind tunnel experiment design from a NASA pioneer in experimental aeronautics Promises cost savings through increased efficiency Incorporates new tactics for quality assessment and assurance, designed to reduce the experimental uncertainty in wind tunnel testing Includes coverage of essential knowledge and first-principles alongside practical examples, insights, guidance and limitations to facilitate successful application in your research and testing
Download or read book The Modern Design of Experiments for Wind Tunnel Testing written by Richard DeLoach and published by Academic Press. This book was released on 2017-09-01 with total page 608 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Modern Design of Experiments for Wind Tunnel Testing: A Practitioner's Guide to Formal Experiment Design for Low-Cost, High-Quality Testing in Experimental Aeronautics covers the background theory needed by those unfamiliar with Design of Experiments (DOE) methods, using detailed examples from decades of work at NASA Langley to demonstrate practical realities, applications and limitations. Pioneering NASA research scientist Richard DeLoach shares theoretical background, unrivalled practical experience and detailed examples of a new approach to aeronautical wind tunnel test design. Understanding the needs of wind tunnel practitioners faced with insufficient resources for, and disappointingly unreliable results through, traditional One Factor At a Time (OFAT) testing, DeLoach has spent decades honing his take on the established Design of Experiments (DOE) approach and applying it to aeronautical testing in a wind tunnel setting. His papers on Modern Design of Experiments (MDOE) relating to experimental aeronautics have won him numerous AIAA 'Outstanding Paper' and 'Best Paper' accolades, as well as a NASA Exceptional Technology Achievement Medal in 2005. In this ground-breaking new book, DeLoach examines the massive potential for cost savings and quality improvement through DOE methods of testing, driving great interest in the topic within the aerospace community. The book is an essential reference to this novel approach from an experienced leader in the field. Offers a true practitioner's guide to this new approach to wind tunnel experiment design from a NASA pioneer in experimental aeronautics Promises cost savings through increased efficiency Incorporates new tactics for quality assessment and assurance, designed to reduce the experimental uncertainty in wind tunnel testing Includes coverage of essential knowledge and first-principles alongside practical examples, insights, guidance and limitations to facilitate successful application in your research and testing
Download or read book N A S A Langley Field Wind Tunnel Apparatus written by F. H. Norton and published by . This book was released on 1921 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt:
