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  • Industrial Chemistry  (296)
  • Inorganic Chemistry  (203)
  • Aeronautics (General)
  • Seismology
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  • 2005-2009  (37)
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  • 1
    Publication Date: 2017-04-03
    Description: We describe and discuss some activities of our working group to disseminate scientific issues concerning seismology to the students of the Region Liguria.
    Description: Published
    Description: Rimini, Italy
    Description: 5.9. Formazione e informazione
    Description: open
    Keywords: Education ; Seismology ; Preparedness ; 05. General::05.03. Educational, History of Science, Public Issues::05.03.99. General or miscellaneous
    Repository Name: Istituto Nazionale di Geofisica e Vulcanologia (INGV)
    Type: Abstract
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  • 2
    Publication Date: 2022-05-25
    Description: This report describes a preliminary analysis of borehole seismic data to determine VLF/Sub-bottom Seismic Noise in the Atlantic and the preliminary results of finite difference modelling for a Cape Fear environment. Noise levels were not a simple function of depth and there are indications that noise levels may depend on local geology about a given receiver position and/or on clamping. Coherency of the noise was generally poor (〈0.8) and was independent of depth. There is no evidence for distinct polarizations or directionality of the noise. The lowest determined value for ambient noise power on the vertical component was 10-4 nm2/Hz in the frequency range from 5-50 Hz. The better clamped horizontal component had comparable power values. In conclusion, although the drill ship was on the site and drill pipe was in the hole, analysis of the data for a large number of windows can provide meaningful upper bounds on the ambient noise levels in the upper crust.
    Description: Prepared for the Naval Ocean Research and Development Activity as the final report for Contract Purchase Order No. N62306-86-l4-7589
    Keywords: Ambient sounds ; Seismology
    Repository Name: Woods Hole Open Access Server
    Type: Working Paper
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  • 3
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    In:  CASI
    Publication Date: 2018-06-06
    Description: This viewgraph presentation describes a general overview of Dryden Flight Research Center. Strategic partnerships, Dryden's mission activity, exploration systems and aeronautics research programs are also described.
    Keywords: Aeronautics (General)
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  • 4
    Publication Date: 2019-07-13
    Description: An overview of the NASA Fundamental Aeronautics Program (FAP) mission and goals is presented. One of the subprograms under the FAP, the Subsonic Fixed Wing Project (SFW), is the focus of the presentation. The SFW system environmental metrics are discussed, along with highlights of planned, systematic approach to research to reduce the environmental impact of commercial aircraft in the areas of acoustics, fuel burn and emissions. The presentation then focuses on collaborative research being conducted with U.S. Industry on the Ultra High Bypass (UHB) engine cycle, the propulsion cycle selected by the SFW to meet the system goals. The partnerships with General Electric Aviation to investigate Open Rotor propulsion concepts and with Pratt & Whitney to investigate the Geared Turbofan UHB engine are highlighted, including current and planned future collaborative research activities with NASA and each organization.
    Keywords: Aeronautics (General)
    Type: E-17352 , 15th AIAA Conference; May 11, 2009 - May 13, 2009; Miami, FL; United States
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  • 5
    Publication Date: 2019-07-13
    Description: This study used a human-in-the-loop simulation to examine the feasibility of mixed equipage operations in an automated separation assurance environment under higher traffic densities. The study involved two aircraft equipage alternatives - with and without data link- and four traffic conditions. In all traffic conditions the unequipped traffic count was increased linearly throughout the scenario from approximately 5 to 20 aircraft. Condition One consisted solely of this unequipped traffic, while the remaining three conditions also included a constant number of equipped aircraft operating within the same airspace: 15 equipped aircraft in condition two, 30 in condition three, and 45 in condition four. If traffic load became excessive during any run, participants were instructed to refuse sector entry to inbound unequipped aircraft until sector load became manageable. Results showed a progressively higher number of unequipped aircraft turned away under the second, third, and fourth scenario conditions. Controller workload also increased progressively. Participants rated the mixed operations concept as acceptable, with some qualifications about procedures and information displays. These results showed that mixed operations might be feasible in the same airspace, if unequipped aircraft count is held to a workable level. This level will decrease with increasing complexity. The results imply that integrated airspace configuration is feasible to a limit. The results also indicate that the conflict detection and resolution automation, equipage, and traffic density are important factors that will need to be considered for airspace configuration.
    Keywords: Aeronautics (General)
    Type: ARC-E-DAA-TN561 , Eighth USA/Europe Air Traffic Management Research and Development Seminar (ATM2009); Jun 29, 2009 - Jul 02, 2009; Napa, CA; United States
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  • 6
    Publication Date: 2019-07-13
    Description: The NASA Fundamental Aeronautics Hypersonics project is focused on technologies for combined cycle, airbreathing propulsions systems to enable reusable launch systems for access to space. Turbine Based Combined Cycle (TBCC) propulsion systems offer specific impulse (Isp) improvements over rocket-based propulsion systems in the subsonic takeoff and return mission segments and offer improved safety. The potential to realize more aircraft-like operations with expanded launch site capability and reduced system maintenance are additional benefits. The most critical TBCC enabling technologies as identified in the National Aeronautics Institute (NAI) study were: 1) mode transition from the low speed propulsion system to the high speed propulsion system, 2) high Mach turbine engine development, 3) transonic aero-propulsion performance, 4) low-Mach-number dual-mode scramjet operation, 5) innovative 3-D flowpath concepts and 6) innovative turbine based combined cycle integration. To address several of these key TBCC challenges, NASA s Hypersonics project (TBCC Discipline) initiated an experimental mode transition task that includes an analytic research endeavor to assess the state-of-the-art of propulsion system performance and design codes. This initiative includes inlet fluid and turbine performance codes and engineering-level algorithms. This effort has been focused on the Combined Cycle Engine Large-Scale Inlet Mode Transition Experiment (CCE LIMX) which is a fully integrated TBCC propulsion system with flow path sizing consistent with previous NASA and DoD proposed Hypersonic experimental flight test plans. This experiment is being tested in the NASA-GRC 10 x 10 Supersonic Wind Tunnel (SWT) Facility. The goal of this activity is to address key hypersonic combined-cycle-engine issues: (1) dual integrated inlet operability and performance issues unstart constraints, distortion constraints, bleed requirements, controls, and operability margins, (2) mode-transition constraints imposed by the turbine and the ramjet/scramjet flow paths (imposed variable geometry requirements), (3) turbine engine transients (and associated time scales) during transition, (4) high-altitude turbine engine re-light, and (5) the operating constraints of a Mach 3-7 combustor (specific to the TBCC). The model will be tested in several test phases to develop a unique TBCC database to assess and validate design and analysis tools and address operability, integration, and interaction issues for this class of advanced propulsion systems. The test article and all support equipment is complete and available at the facility. The test article installation and facility build-up in preparation for the inlet performance and operability characterization is near completion and testing is planned to commence in FY11.
    Keywords: Aeronautics (General)
    Type: E-17652 , 2009 Annual Meeting; Sep 29, 2009 - Oct 01, 2009; Atlanta, GA; United States
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  • 7
    Publication Date: 2019-07-12
    Description: The Advanced Noise Control Fan at the NASA Glenn Research Center is used to experimentally analyze fan generated acoustics. In order to determine how a proposed noise reduction concept affects fan performance, flow measurements can be used to compute mass flow. Since tedious flow mapping is required to obtain an accurate mass flow, an equation was developed to correlate the mass flow to inlet lip wall static pressure measurements. Once this correlation is obtained, the mass flow for future configurations can be obtained from the nonintrusive wall static pressures. Once the mass flow is known, the thrust and fan performance can be evaluated. This correlation enables fan acoustics and performance to be obtained simultaneously without disturbing the flow.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215807 , E-17070
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  • 8
    Publication Date: 2019-07-12
    Description: Rotating disks undergo rigorous mechanical loading conditions that make them subject to a variety of failure mechanisms leading to structural deformities and cracking. During operation, periodic loading fluctuations and other related factors cause fractures and hidden internal cracks that can only be detected via noninvasive types of health monitoring and/or nondestructive evaluation. These evaluations go further to inspect material discontinuities and other irregularities that have grown to become critical defects that can lead to failure. Hence, the objectives of this work is to conduct a collective analytical and experimental study to present a well-rounded structural assessment of a rotating disk by means of a health monitoring approach and to appraise the capabilities of an in-house rotor spin system. The analyses utilized the finite element method to analyze the disk with and without an induced crack at different loading levels, such as rotational speeds starting at 3000 up to 10 000 rpm. A parallel experiment was conducted to spin the disk at the desired speeds in an attempt to correlate the experimental findings with the analytical results. The testing involved conducting spin experiments which, covered the rotor in both damaged and undamaged (i.e., notched and unnotched) states. Damaged disks had artificially induced through-thickness flaws represented in the web region ranging from 2.54 to 5.08 cm (1 to 2 in.) in length. This study aims to identify defects that are greater than 1.27 cm (0.5 in.), applying available means of structural health monitoring and nondestructive evaluation, and documenting failure mechanisms experienced by the rotor system under typical turbine engine operating conditions.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215675 , E-17038
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  • 9
    Publication Date: 2019-07-12
    Description: Very large eddy simulation (VLES) of the nonreacting turbulent flow in a single-element lean direct injection (LDI) combustor has been successfully performed via the approach known as the partially resolved numerical simulation (PRNS/VLES) using a nonlinear subscale model. The grid is the same as the one used in a previous RANS simulation, which was considered as too coarse for a traditional LES simulation. In this study, we first carry out a steady RANS simulation to provide the initial flow field for the subsequent PRNS/VLES simulation. We have also carried out an unsteady RANS (URANS) simulation for the purpose of comparing its results with that of the PRNS/VLES simulation. In addition, these calculated results are compared with the experimental data. The present effort has demonstrated that the PRNS/VLES approach, while using a RANS type of grid, is able to reveal the dynamically important, unsteady large-scale turbulent structures occurring in the flow field of a single-element LDI combustor. The interactions of these coherent structures play a critical role in the dispersion of the fuel, hence, the mixing between the fuel and the oxidizer in a combustor.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215644 , E-16956
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  • 10
    Publication Date: 2019-08-13
    Description: Results of an experimental study are presented on the effectiveness of a vortex generator (VG) in preventing lift-off of a jet-in-cross-flow (JICF). The study is pertinent to film-cooling applications and its relevance to NASA programs is first briefly discussed. In the experiment, the jet issues into the boundary layer at an angle of 20deg to the free-stream. The effect of a triangular, ramp-shaped VG is studied while varying its geometry and location. Detailed flow-field properties are obtained for a case in which the height of the VG and the diameter of the orifice are comparable to the approach boundary layer thickness. The VG produces a streamwise vortex pair with vorticity magnitude three times larger (and of opposite sense) than that found in the JICF alone. Such a VG appears to be most effective in keeping the jet attached to the wall. The effect of parametric variation is studied mostly from surveys ten diameters downstream from the orifice. Results over a range of jet-to-freestream momentum flux ratio (1〈J〈11) show that the VG has a significant effect even at the highest J covered in the experiment. When the VG height is halved there is a lift-off of the jet. On the other hand, when the height is doubled, the jet core is dissipated due to larger turbulence intensity. Varying the location of the VG, over a distance of three diameters from the orifice, is found to have little impact.
    Keywords: Aeronautics (General)
    Type: E-17584 , NASA''s Fundamental Aeronautics 2009 Technical Conference: Subsonic Fixed Wing Project; Sep 29, 2009 - Oct 01, 2009; Atlanta, GA; United States
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  • 11
    Publication Date: 2019-08-28
    Description: The National Aeronautics and Space Act of 1958 directed the annual Aeronautics and Space Report to include a "comprehensive description of the programmed activities and the accomplishments of all agencies of the United States in the field of aeronautics and space activities during the preceding calendar year." In recent years, the reports have been prepared on a fiscal-year basis, consistent with the budgetary period now used in programs of the Federal Government. This year's report covers activities that took place from October 1, 2007, through September 30, 2008.
    Keywords: Aeronautics (General)
    Type: NASA/NP-2009-05-581-HQ
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  • 12
    Publication Date: 2019-07-13
    Description: In this paper the design and modeling of a sensor system that gives relative position measurements is described. The position is provided in the form of bearing and range to a retro target placed on a far field target.
    Keywords: Aeronautics (General)
    Type: AIAA Guidance, Navigation and Control Conference and Exhibit; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 13
    Publication Date: 2019-07-13
    Description: Simulation environments have been an integral part of Cassini's heritage. From the time of flight software development and testing to the beginning of the spacecraft's extended mission operations, both softsim and hardware-in-the-loop testbeds have played vital roles in verifying and validating key mission events. Satellite flybys and mission-critical events have established the need to model Titan's atmospheric torque, Enceladus' plume density, and other key parametric spacecraft environments. This paper will focus on enhancements to Cassini's Flight Software Development System (FSDS) and Integrated Test Laboratory (ITL) to model key event attributes which establish valid test environments and ensure safe spacecraft operability. Comparisons between simulated to in-flight data are presented which substantiate model validity.
    Keywords: Aeronautics (General)
    Type: AIAA Guidance, Navigation and Control Conference and Exhibit; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 14
    Publication Date: 2019-07-12
    Description: This paper provides an overview of rotorcraft crashworthiness research being conducted at NASA Langley Research Center under sponsorship of the Subsonic Rotary Wing (SRW) Aeronautics Program. The research is focused in two areas: development of an externally deployable energy attenuating concept and improved prediction of rotorcraft crashworthiness. The deployable energy absorber (DEA) is a composite honeycomb structure, with a unique flexible hinge design that allows the honeycomb to be packaged and remain flat until needed for deployment. The capabilities of the DEA have been demonstrated through component crush tests and vertical drop tests of a retrofitted fuselage section onto different surfaces or terrain. The research on improved prediction of rotorcraft crashworthiness is focused in several areas including simulating occupant responses and injury risk assessment, predicting multi-terrain impact, and utilizing probabilistic analysis methods. A final task is to perform a system-integrated simulation of a full-scale helicopter crash test onto a rigid surface. A brief description of each research task is provided along with a summary of recent accomplishments.
    Keywords: Aeronautics (General)
    Type: LF99-6817
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  • 15
    Publication Date: 2019-07-12
    Description: The ability of kappa-omega models to predict compressible turbulent skin friction in hypersonic boundary layers is investigated. Although uncorrected two-equation models can agree well with correlations for hot-wall cases, they tend to perform progressively worse - particularly for cold walls - as the Mach number is increased in the hypersonic regime. Simple algebraic models such as Baldwin-Lomax perform better compared to experiments and correlations in these circumstances. Many of the compressibility corrections described in the literature are summarized here. These include corrections that have only a small influence for kappa-omega models, or that apply only in specific circumstances. The most widely-used general corrections were designed for use with jet or mixing-layer free shear flows. A less well-known dilatation-dissipation correction intended for boundary layer flows is also tested, and is shown to agree reasonably well with the Baldwin-Lomax model at cold-wall conditions. It exhibits a less dramatic influence than the free shear type of correction. There is clearly a need for improved understanding and better overall physical modeling for turbulence models applied to hypersonic boundary layer flows.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215705 , L-19589 , LF99-8457
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  • 16
    Publication Date: 2019-07-13
    Description: Worldwide concerns of air quality and climate change have made environmental protection one of the most critical issues in aviation today. NASA s current Fundamental Aeronautics Research program is directed at three generations of aircraft in the near, mid and far term, with initial operating capability around 2015, 2020, and 2030, respectively. Each generation has associated goals for fuel burn, NOx, noise, and field-length reductions relative to today s aircrafts. The research for the 2020 generation is directed at enabling a hybrid wing body (HWB) aircraft to meet NASA s aggressive technology goals. This paper presents the conceptual cycle and mechanical designs of the two engine concepts, podded and embedded systems, which were proposed for a HWB cargo freighter. They are expected to offer significant benefits in noise reductions without compromising the fuel burn.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215680 , GT2009-59568 , ARL-TR-4719 , E-16910-1 , ASME Turbo 2009; Jun 08, 2009 - Jun 12, 2009; Orlando, FL; United States
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  • 17
    Publication Date: 2019-07-13
    Description: The American Institute of Aeronautics Astronautics (AIAA) Modeling and Simulation Technical Committee is in final preparation of a new standard for the exchange of flight dynamics models. The standard will become an ANSI standard and is under consideration for submission to ISO for acceptance by the international community. The standard has some a spects that should provide benefits to the simulation training community. Use of the new standard by the training simulation community will reduce development, maintenance and technical refresh investment on each device. Furthermore, it will significantly lower the cost of performing model updates to improve fidelity or expand the envelope of the training device. Higher flight fidelity should result in better transfer of training, a direct benefit to the pilots under instruction. Costs of adopting the standard are minimal and should be paid back within the cost of the first use for that training device. The standard achie ves these advantages by making it easier to update the aerodynamic model. It provides a standard format for the model in a custom eXtensible Markup Language (XML) grammar, the Dynamic Aerospace Vehicle Exchange Markup Language (DAVE-ML). It employs an existing XML grammar, MathML, to describe the aerodynamic model in an input data file, eliminating the requirement for actual software compilation. The major components of the aero model become simply an input data file, and updates are simply new XML input files. It includes naming and axis system conventions to further simplify the exchange of information.
    Keywords: Aeronautics (General)
    Type: 9019-0929-0301 , LF99-9097 , Interservice/Industry Training, Simulation and Education Conference (I/ITSEC 2009); Nov 30, 2009 - Dec 03, 2009; Orlando, FL; United States
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  • 18
    Publication Date: 2019-07-13
    Description: This slide presentation reviews the Airborne Science Program and the platforms used for conducting investigations for the Earth System Science. Included is a chart that shows some of the aircraft and the operational altitude and the endurance of the aircraft, views of the Dryden Aircraft Operation Facility, and some of the current aircraft that the facility operates, and the varieties of missions that are flown and the type of instrumentation. Also included is a chart showing the attributes of the various aircraft (i.e., duration, weight for a payload, maximum altitude, airspeed and range) for comparison
    Keywords: Aeronautics (General)
    Type: DFRC-1084 , Keck Institute for Space Studies (KISS) Exoplanet 2009 Workshop; Nov 09, 2009 - Nov 13, 2009; Pasadena, CA; United States
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  • 19
    Publication Date: 2019-07-13
    Description: This poster reviews the collarborative research approaches that NASA has been designing and implementing for the Integrated Vehicle Health Management (IVHM) Project. The inputs for the technical plan are reviewed, the Research Test and Integration Plan (RTIP) WIKI, is used to create and propose a multi-themed and multi-partner research testing opportunities. The outputs are testing opportunities.
    Keywords: Aeronautics (General)
    Type: DFRC-1091 , NASA ARMD/Aviation Safety Technical Conference; Nov 17, 2009 - Nov 19, 2009; McLean, VA; United States
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  • 20
    Publication Date: 2019-07-13
    Description: The Cruise Efficient Short Take-Off and Landing (CESTOL) aircraft and Civil Tiltrotor (CTR) are two examples of powered-lift aircraft concepts that are of interest to NASA. These concepts will be able to utilize the shorter unused or underutilized runways and corresponding airspace at the crowded hub airports and many unused airfields and airspace that currently exist in other expanding urban areas providing additional capacity to the airspace system and reductions in congestion and delays seen in the current system. By treating the use of CESTOL and CTR as critical components that supplement other green aircraft to be used in the overall airspace system, the efficiency and improvements gained by the entire system will offset the potential increased fuel usage and emissions that may be a result of providing short field capability to the powered-lift aircraft. My presentation will address how NASA and the aerospace industry may identify, analysis, and finally implement these powered-lift aircraft into the airspace system and improve the capacity and reduce delay, while obtaining an overall reduction in noise, fuel usage, and emissions.
    Keywords: Aeronautics (General)
    Type: ARC-E-DAA-TN554 , Green Aviation Workshop; Apr 25, 2009 - Apr 26, 2009; Moffett Field, CA; United States
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  • 21
    Publication Date: 2019-07-13
    Description: This paper has two objectives. The first objective is to formulate a 3-dimensional Finite Element Model for the dynamic analysis of helicopter rotor blades. The second objective is to implement and analyze a dual-primal iterative substructuring based Krylov solver, that is parallel and scalable, for the solution of the 3-D FEM analysis. The numerical and parallel scalability of the solver is studied using two prototype problems - one for ideal hover (symmetric) and one for a transient forward flight (non-symmetric) - both carried out on up to 48 processors. In both hover and forward flight conditions, a perfect linear speed-up is observed, for a given problem size, up to the point of substructure optimality. Substructure optimality and the linear parallel speed-up range are both shown to depend on the problem size as well as on the selection of the coarse problem. With a larger problem size, linear speed-up is restored up to the new substructure optimality. The solver also scales with problem size - even though this conclusion is premature given the small prototype grids considered in this study.
    Keywords: Aeronautics (General)
    Type: ARC-E-DAA-TN483 , American Helicopter Society 65th Annual Forum; May 27, 2009 - May 29, 2009; Grapevine, TX; United States
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  • 22
    Publication Date: 2019-07-13
    Description: Atmospheric turbulence cueing produced by flight simulator motion systems has been less than satisfactory because the turbulence profiles have been attenuated by the motion cueing algorithms. Cardullo and Ellor initially addressed this problem by directly porting the turbulence model output to the motion system. Reid and Robinson addressed the problem by employing a parallel aircraft model, which is only stimulated by the turbulence inputs and adding a filter specially designed to pass the higher turbulence frequencies. There have been advances in motion cueing algorithm development at the Man-Machine Systems Laboratory, at SUNY Binghamton. In particular, the system used to generate turbulence cues has been studied. The Reid approach, implemented by Telban and Cardullo, was employed to augment the optimal motion cueing algorithm installed at the NASA LaRC Simulation Laboratory, driving the Visual Motion Simulator. In this implementation, the output of the primary flight channel was added to the output of the turbulence channel and then sent through a non-linear cueing filter. The cueing filter is an adaptive filter; therefore, it is not desirable for the output of the turbulence channel to be augmented by this type of filter. The likelihood of the signal becoming divergent was also an issue in this design. After testing on-site it became apparent that the architecture of the turbulence algorithm was generating unacceptable cues. As mentioned above, this cueing algorithm comprised a filter that was designed to operate at low bandwidth. Therefore, the turbulence was also filtered, augmenting the cues generated by the model. If any filtering is to be done to the turbulence, it will utilize a filter with a much higher bandwidth, above the frequencies produced by the aircraft response to turbulence. The authors have developed an implementation wherein only the signal from the primary flight channel passes through the nonlinear cueing filter. This paper discusses three new algorithms. Testing shows that the new methods provide the pilot with a more realistic sensation of turbulence; the cues are not attenuated by algorithm. Results of offline testing show the credibility of the models. Offline test verification was based primarily on the evaluation of the power spectral density of the outputs and the time response.
    Keywords: Aeronautics (General)
    Type: AIAA Paper 2009-6247 , LF99-9191 , AIAA Modeling and Simulation Technologies Conference; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 23
    Publication Date: 2019-07-13
    Description: This slide presentation reviews some of the projects that have extended NASA Dryden's capabilities in designing, testing, and using Unmanned Aerial Vehicles (UAV's). Some of the UAV's have been for Science and experimental applications, some have been for flight research and demonstration purposes, and some have been small UAV's for other customers.
    Keywords: Aeronautics (General)
    Type: DFRC-1055 , UCSD Seminar; Aug 26, 2009; San Diego, CA; United States
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  • 24
    Publication Date: 2019-07-13
    Description: An investigation of effectiveness of the reaction control system (RCS) of Mars Science Laboratory (MSL) entry capsule during atmospheric flight has been conducted. The reason for the investigation is that MSL is designed to fly a lifting actively guided entry with hypersonic bank maneuvers, therefore an understanding of RCS effectiveness is required. In the course of the study several jet configurations were evaluated using Langley Aerothermal Upwind Relaxation Algorithm (LAURA) code, Data Parallel Line Relaxation (DPLR) code, Fully Unstructured 3D (FUN3D) code and an Overset Grid Flowsolver (OVERFLOW) code. Computations indicated that some of the proposed configurations might induce aero-RCS interactions, sufficient to impede and even overwhelm the intended control torques. It was found that the maximum potential for aero-RCS interference exists around peak dynamic pressure along the trajectory. Present analysis largely relies on computational methods. Ground testing, flight data and computational analyses are required to fully understand the problem. At the time of this writing some experimental work spanning range of Mach number 2.5 through 4.5 has been completed and used to establish preliminary levels of confidence for computations. As a result of the present work a final RCS configuration has been designed such as to minimize aero-interference effects and it is a design baseline for MSL entry capsule.
    Keywords: Aeronautics (General)
    Type: LF99-7145 , 47th AIAA Aerospace Sciences Meeting and Exhibit; Jan 05, 2009 - Jan 08, 2009; Orlando, FL; United States
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  • 25
    Publication Date: 2019-07-13
    Description: This report gives an overview of physical modeling enhancements to the Wind-US flow solver which were made to improve the capabilities for simulation of hypersonic flows and the reliability of computations to complement hypersonic testing. The improvements include advanced turbulence models, a bypass transition model, a conjugate (or closely coupled to vehicle structure) conduction-convection heat transfer capability, and an upgraded high-speed combustion solver. A Mach 5 shock-wave boundary layer interaction problem is used to investigate the benefits of k- s and k-w based explicit algebraic stress turbulence models relative to linear two-equation models. The bypass transition model is validated using data from experiments for incompressible boundary layers and a Mach 7.9 cone flow. The conjugate heat transfer method is validated for a test case involving reacting H2-O2 rocket exhaust over cooled calorimeter panels. A dual-mode scramjet configuration is investigated using both a simplified 1-step kinetics mechanism and an 8-step mechanism. Additionally, variations in the turbulent Prandtl and Schmidt numbers are considered for this scramjet configuration.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215615 , AIAA-2009-193 , E-16931 , 47th Aerospace Sciences Meeting; Jan 05, 2009 - Jan 08, 2009; Orlando, Fl; United States
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  • 26
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    In:  CASI
    Publication Date: 2019-07-13
    Description: This slide presentation reviews the status of several NASA Dryden projects. These include: the Lift And Nozzle Change Effects on Tail Shock (LANCETS), Integrated Resilient Aircraft Control (IRAC) F-18 #853 Testbed X-48B, Blended Wing Body flights, Stratospheric Observatory for Infrared Astronomy (SOFIA), Ikhana Project, and the Orion Crew Exploration Vehicle (CEV) Launch Abort Systems Tests
    Keywords: Aeronautics (General)
    Type: DFRC-957 , Aerospace Control and Guidance Systems Committee Meeting 103; Feb 25, 2009 - Feb 27, 2009; Seattle, WA; United States
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  • 27
    Publication Date: 2019-07-13
    Description: This slide presentation reviews the objectives of the Multidisciplinary Analysis and Technology Development (MDATD) in the Subsonic Rotary Wing project. The objectives are to integrate technologies and analyses to enable advanced rotorcraft and provide a roadmap to guide Level 1 and 2 research. The MDATD objectives will be met by conducting assessments of advanced technology benefits, developing new or enhanced design tools, and integrating Level 2 discipline technologies to develop and enable system-level analyses and demonstrations.
    Keywords: Aeronautics (General)
    Type: ARC-E-DAA-TN848 , 2009 Fundamental Aeronautics Program Annual Meeting; Sep 09, 2009 - Oct 01, 2009; Atlanta, GA; United States
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  • 28
    Publication Date: 2019-07-13
    Description: A computational fluid dynamics study is conducted to examine nozzle exhaust jet plume effects on the Sonic boom signature of a supersonic aircraft. A simplified axisymmetric nozzle geometry, representative of the nozzle on the NASA Dryden NF-15B Lift and Nozzle Change Effects on Tail Shock research airplane, is considered. The computational fluid dynamics code is validated using available wind-tunnel sonic boom experimental data. The effects of grid size, spatial order of accuracy. grid type, and flow viscosity on the accuracy of the predicted sonic boom pressure signature are quantified. Grid lines parallel to the Mach wave direction are found to give the best results. Second-order accurate upwind methods are required as a minimum for accurate sonic boom simulations. The highly underexpanded nozzle flow is found to provide significantly more reduction in the tail shock strength in the sonic boom N-wave pressure signature than perfectly expanded and overexpanded nozzle flows. A tail shock train in the sonic boom signature is observed for the highly underexpanded nozzle flow. Axisymmetric computational fluid dynamics simulations show the flow physics inside the F-15 nozzle to be nonisentropic and complex.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-214650 , AIAA Paper 2009-1054 , H-2923 , DFRC-938 , 47th AIAA Aerospace Sciences meeting; Jan 05, 2009 - Jan 08, 2009; Orlando, FL; United States
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  • 29
    Publication Date: 2019-07-12
    Description: The desire for higher engine efficiency has resulted in the evolution of aircraft gas turbine engines from turbojets, to low bypass ratio, first generation turbofans, to today's high bypass ratio turbofans. Although increased bypass ratio has clear benefits in terms of propulsion system metrics such as specific fuel consumption, these benefits may not translate into aircraft system level benefits due to integration penalties. In this study, the design trade space for advanced turbofan engines applied to a single aisle transport (737/A320 class aircraft) is explored. The benefits of increased bypass ratio and associated enabling technologies such as geared fan drive are found to depend on the primary metrics of interest. For example, bypass ratios at which mission fuel consumption is minimized may not require geared fan technology. However, geared fan drive does enable higher bypass ratio designs which result in lower noise. The results of this study indicate the potential for the advanced aircraft to realize substantial improvements in fuel efficiency, emissions, and noise compared to the current vehicles in this size class.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215784 , L-19712 , LF-9138
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  • 30
    Publication Date: 2019-07-12
    Description: Improved and/or accelerated decision making is a crucial step during flutter certification processes. Unfortunately, most finite element structural dynamics models have uncertainties associated with model validity. Tuning the finite element model using measured data to minimize the model uncertainties is a challenging task in the area of structural dynamics. The model tuning process requires not only satisfactory correlations between analytical and experimental results, but also the retention of the mass and stiffness properties of the structures. Minimizing the difference between analytical and experimental results is a type of optimization problem. By utilizing the multidisciplinary design, analysis, and optimization (MDAO) tool in order to optimize the objective function and constraints; the mass properties, the natural frequencies, and the mode shapes can be matched to the target data to retain the mass matrix orthogonality. This approach has been applied to minimize the model uncertainties for the structural dynamics model of the aerostructures test wing (ATW), which was designed and tested at the National Aeronautics and Space Administration Dryden Flight Research Center (Edwards, California). This study has shown that natural frequencies and corresponding mode shapes from the updated finite element model have excellent agreement with corresponding measured data.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-214646 , H-2942 , DFRC-963
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  • 31
    Publication Date: 2019-07-13
    Description: This paper presents the results of an activity by the Large Eddy Simulation (LES) Working Group of the AIAA Fluid Dynamics Technical Committee to (1) address the current capabilities of LES, (2) outline recommended practices and key considerations for using LES, and (3) identify future research needs to advance the capabilities and reliability of LES for analysis of turbulent flows. To address the current capabilities and future needs, a survey comprised of eleven questions was posed to LES Working Group members to assemble a broad range of perspectives on important topics related to LES. The responses to these survey questions are summarized with the intent not to be a comprehensive dictate on LES, but rather the perspective of one group on some important issues. A list of recommended practices is also provided, which does not treat all aspects of a LES, but provides guidance on some of the key areas that should be considered.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215616 , AIAA-2009-948 , E-16932 , 47th Aerospace Sciences Meeting; Jan 05, 2009 - Jan 08, 2009; Orlando, FL; United States
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  • 32
    Publication Date: 2019-07-13
    Description: An experiment was performed to assess CFD modeling of a hypersonic-vehicle breach, boundary-layer flow ingestion and internal surface impingement. Tests were conducted in the NASA Langley Research Center 31-Inch Mach 10 Tunnel. Four simulated breaches were tested and impingement heat flux data was obtained for each case using both phosphor thermography and thin film gages on targets placed inside the model. A separate target was used to measure the surface pressure distribution. The measured jet impingement width and peak location are in good agreement with CFD analysis.
    Keywords: Aeronautics (General)
    Type: LF99-8070 , 41st AIAA Thermophysics Conference; Jun 22, 2009 - Jun 25, 2009; Texas; United States
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  • 33
    Publication Date: 2019-07-13
    Description: Due to unprecedented extent and flexibility of the coverage that is now attainable both in space and time, stratospheric unmanned aircraft, such as the Global Hawk (GH), offers new opportunities for the study of climate changes. The capability of performing long flights at altitudes close to the boundary conditions of radiative processes, and of following the diurnal variation of chemical species and clouds, make the GH competitive with LEO and geosynchronous satellites, and even capable of new observations that are not possible from satellites. This paper discusses how the GH can be used to make relevant advancements in most of the issues that are related to climate change studies, such as: Earth Radiation Budget, Water Cycle, Ecosystems and Upper Troposphere-Lower Stratosphere, as well as to the monitoring and control of Greenhouse Gases and Air Quality . Collaboration between NASA and Italian scientific institutions, within the framework of the US.-Italy Cooperation on Climate Change, is providing the opportunity to rapidly deploy new instruments on the GH and to possibly operate the aircraft from an Italian site in the Mediterranean area. From this area, which is considered highly vulnerable to climate change, meridional transects would allow the crossing of Polar and Sub Tropical Jets, as well as a complete crossing of the Inter Tropical Convergence Zone, while latitudinal ones would follow the influx from Asia and North America. Regions otherwise difficult to access, such as Central Africa and the Tibetan Plateau, could be reached and better investigated. An overview of these new opportunities will be given and discussed.
    Keywords: Aeronautics (General)
    Type: DFRC-921 , 33rd International Symposium on Remote Sensing of Environment; May 04, 2009 - May 08, 2009; Stresa; Italy
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  • 34
    Publication Date: 2019-07-13
    Description: The internal flow structure in a specific fluidic diverter is studied over a range from low subsonic to sonic inlet conditions by a time-dependent numerical analysis. The understanding will aid in the development of fluidic diverters with minimum pressure losses and advanced designs of flow control actuators. The velocity, temperature and pressure fields are calculated for subsonic conditions and the self-induced oscillatory behavior of the flow is successfully predicted. The results of our numerical studies have excellent agreement with our experimental measurements of oscillation frequencies. The acoustic speed in the gaseous medium is determined to be a key factor for up to sonic conditions in governing the mechanism of initiating the oscillations as well as determining its frequency. The feasibility of employing plasma actuation with a minimal perturbation level is demonstrated in steady-state calculations to also produce oscillation frequencies of our own choosing instead of being dependent on the fixed-geometry fluidic device.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-216088 , AIAA Paper 2009-4012 , E-17132 , 39th Fluid Dynamics Conference and Exhibit; Jun 22, 2009 - Jun 25, 2009; San Antonio, TX; United States
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  • 35
    Publication Date: 2019-07-13
    Description: The Mars Entry Atmospheric Data System (MEADS) is being developed as part of the Mars Science Laboratory (MSL), Entry, Descent, and Landing Instrumentation (MEDLI) project. The MEADS project involves installing an array of seven pressure transducers linked to ports on the MSL forebody to record the surface pressure distribution during atmospheric entry. These measured surface pressures are used to generate estimates of atmospheric quantities based on modeled surface pressure distributions. In particular, the quantities to be estimated from the MEADS pressure measurements include the total pressure, dynamic pressure, Mach number, angle of attack, and angle of sideslip. Secondary objectives are to estimate atmospheric winds by coupling the pressure measurements with the on-board Inertial Measurement Unit (IMU) data. This paper provides details of the algorithm development, MEADS system performance based on calibration, and uncertainty analysis for the aerodynamic and atmospheric quantities of interest. The work presented here is part of the MEDLI performance pre-flight validation and will culminate with processing flight data after Mars entry in 2012.
    Keywords: Aeronautics (General)
    Type: AIAA Paper 2009-3916 , LF99-8954 , 41st AIAA Thermophysics Conference; Jun 22, 2009 - Jun 25, 2009; San Antonio, TX; United States
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  • 36
    Publication Date: 2019-07-13
    Description: Optimization of rotorcraft flowfields using an adjoint method generally requires a time-dependent implementation of the equations. The current study examines an intermediate approach in which a subset of rotor flowfields are cast as steady problems in a noninertial reference frame. This technique permits the use of an existing steady-state adjoint formulation with minor modifications to perform sensitivity analyses. The formulation is valid for isolated rigid rotors in hover or where the freestream velocity is aligned with the axis of rotation. Discrete consistency of the implementation is demonstrated using comparisons with a complex-variable technique, and a number of single- and multi-point optimizations for the rotorcraft figure of merit function are shown for varying blade collective angles. Design trends are shown to remain consistent as the grid is refined.
    Keywords: Aeronautics (General)
    Type: LF99-8473 , AHS International 65th Forum and Technology Display; May 27, 2009 - May 29, 2009; Grapevine, TX; United States
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  • 37
    Publication Date: 2019-07-13
    Description: This slide presentation reviews the Global Hawk, a unmanned aerial vehicle (UAV) that NASA plans to use for Earth Sciences research. The Global Hawk is the world's first fully autonomous high-altitude, long-endurance aircraft, and is capable of conducting long duration missions. Plans are being made for the use of the aircraft on missions in the Arctic, Pacific and Western Atlantic Oceans. There are slides showing the Global Hawk Operations Center (GHOC), Flight Control and Air Traffic Control Communications Architecture, and Payload Integration and Accommodations on the Global Hawk. The first science campaign, planned for a study of the Pacific Ocean, is reviewed.
    Keywords: Aeronautics (General)
    Type: DFRC-997 , 33rd International Symposium on Remote Sensing of Environment; May 04, 2009 - May 08, 2009; Stresa; Italy
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    Chemie Ingenieur Technik - CIT 21 (1949) 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 6-8 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Notes: Die Anordnung dient zur Messung von Dampfdruckerniedrigungen verdünnter Lösungen (10-3 Mol/l) insbesondere assoziierender Substanzen. Es wurde eine Meßanordnung entwickelt, in der die durch kleine Druckdifferenzen verursachte Ausbuchtung der Wölbung des Meniskus eines Hg-Manometers nach dem Prinzip eines Photometers lichtelektrisch mit einem Vakuumthermoelement gemessen wird. Die Anordnung gestattet unabhängig vom Gesamtdruck noch Druckschwankungen von 10-4 mm Hg zu messen.
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    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
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    Notes: Es werden einige Regeleinrichtungen besprochen, die zum Aufbau von im wesentlichen automatisch arbeitenden Destillationskolonnen sowohl für diskontinuierlichen als auch für kontinuierlichen Betrieb führten.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 1-6 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Unsere wichtigsten chemischen Großsynthesen gehen von Acetylen bzw. vom Kohlenoxyd-Wasserstoff-Gemisch aus. Die Arbeiten im letzten Jahrzehnt bezweckten, diese Rohstoffe unmittelbar aus dem Ferngas zu gewinnen. Von den entwickelten Verfahren verdient insbesondere das Sauerstoff-Verfahren Beachtung. Es liefert ein Synthesegas mit nur noch 0,2% Methan und ist unempfindlich gegen den im Ferngas vorhandenen organischen Schwefel. Eine etwa folgende Umsetzung des Kohlenoxydes mit Wasserdampf zu CO2 und Wasserstoff kann in unmittelbarem Ánschluß an der Kohlenwasserstoff-Spaltung vorgenommen werden, so daß kein neuer Dampfverbrauch auftritt. Während in der folgenden Arbeit über das Verfahren zur Verarbeitung des gesamten Ferngases auf Kohlenoxyd und Wasserstoff berichtet wird, wird in einer weiteren Arbeit die chemische Verwertung der einzelnen Bestandteile des Ferngases behandelt.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 19-24 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Nach den verfügbaren amerikanischen Quellen wird zusammenfassend über die seit etwa 1940 in Amerika erreichten Fortschritte auf dem Gebiet der Sauerstoff-Erzeugung und -Anwendung berichtet, besonders über Versuche an Austauschböden und Trennkolonnen für kleinere, meist leichtbewegliche Anlagen, über die Mittel zur Kälteerzeugung, über die Herstellung und den Versand von flüssigem Sauerstoff sowie über die unmittelbare Erzeugung von hochkomprimiertem Sauerstoff für die Flaschenfüllung durch Verdampfung des flüssigen Sauerstoffs im Zerlegungsapparat. Weiter wird ein neuer Austauschertyp besprochen und auf neu erschlossene Anwendungsgebiete für billigen, mäßig reinen Sauerstoff hingewiesen.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 15-18 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Bei Kohlenoxyd-Hydrierungen unter Drucken zwischen 300 und 1000 at und Temperaturen über 400° erwiesen sich z. T. sog. „kohlenoxydfeste“ metallische Werkstoffe, insbesondere Stähle mit mehr als 13% Chrom, für den praktischen Betrieb als ungeeignet, obwohl sie anscheinend von Kohlenoxyd nicht abgebaut wurden. Es wurden daher 20 derartige Stähle und 6 eisenfreie Metallproben gegenüber Wassergas bei 1000 at und Temperaturen zwischen 300 und 450° untersucht und aus den Ergebnissen Folgerungen für die praktische Verwendungsmöglichkeit im Apparafebau gezogen.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 24-30 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 31-31 
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    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 31-32 
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 33-37 
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    Notes: Die Angabe, daß sich die Ausscheidung von Härtebildern mit Orthophosphaten in wässeriger Lösung unter Bildung von Tricalciumphosphat vollziehe, ist unzutreffend. Der Niederschlag dürfte vielmehr die Formel des Hydroxylapatits haben.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 49-57 
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    Notes: Bis 1940 war die Anwendung hoher Vakua fast nur auf das Laboratorium beschränkt, in der Technik evakuierte nur die Röhrenindustrie bis auf Drucke von beinahe 10-7 mm Hg, aber es handelte sich auch hier meist nur um verhältnismäßig kleine Volumina. Die anschließende Entwicklung wurde durch mehrere Ereignisse besonders gefördert: durch die Konstruktion hervorragender Pumpen in Deutschland und Amerika, durch die Schaffung guter Gläser in Jena, durch die Erfolge der Vakuumdestillation von Fetten, Ölen und empfindlichen organischen Substanzen in England, Deutschland und später in USA, und schließlich durch das amerikanische Atombombenprojekt, wo bereits bei der Gasdiffusions- und elektromagnetischen Trennung der Uran-Isotope die ersten großen Vakuum-Probleme auftraten. Heute ist selbst die großtechnische Erzeugung von Hochvakuum zwischen -100° und + 1000° C ein untergeordnetes Problem der Verfahrenstechnik geworden.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 61-63 
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    Notes: Es wird über Versuche mit zwei Ausführungen von Pilzglocken aus Porzellan berichtet, die in Rektifizierböden eingebaut waren. Wirkung, Druckverlust und Flüssigkeitsinhalt der Sälen wurden ermittelt. Um eine gute Wirkung zu erreichen, müssen die Einzelabmessungen des Bodens entsprechend gewählt werden. Auch der Einbau einer Staurippe erhöht die Bodenwirkung.
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    Notes: Die hier beschriebenen Methoden sollen es dem Schichtarbeiter mit einfachen Mitteln ermöglichen, kurzfristig eine gefährliche Acetylen-Anreicherung zu erkennen. Die Ergebnisse werden mit denen quantitativer Methoden verglichen.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 68-70 
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    Notes: Der im folgenden beschriebene Kolbenverdichter arbeitet mit ungeschmierten Kolben und Stopfbüchsen. Die Abdichtung wird durch Labyrinthdichtungen erreicht. Dadurch behält das verdichtete Medium die ursprüngliche Reinheit, so daß der Verdichter in der chemischen Industrie und der Lebensmittelindustrie da verwendet werden kann, wo völlig reine Druckluft gebraucht wird.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 71-73 
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 68-68 
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    Notes: In den letzten Jahren hat die Fluorchemie, insbesondere die verschiedener organischer fluorierter Verbindungen, erheblich an praktischer Bedeutung gewonnen. Da in einigen Veröffentlichungenz. B. DECHEMA-Werkstofftabellen 1948; ferner Ind. Engng. Chem. 39, 12a u. 91a [1947]. bereits auf die gute Eignung des Silbers als Apparatebauwerkstoff für technische Reaktionen mit Fluorverbindungen hingewiesen worden ist, seien nachstehend einige quantitative Angaben gemasht, die das Ergebnis einer 1944 laboratoriumsmäßig durchgeführten Korrosionsprüfung darsfellen.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 74-74 
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 87-87 
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 89-94 
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    Notes: Die technisch-wissenschaftliche Forschung der letzten Jahrzehnte brachte eine Erweiterung und Vertiefung unserer Erkenntnisse über die beim gekoppelten Wärme- und Stoffaustausch sich abspielenden Vorgänge. Trotzdem blieben noch Fragen ungeklärt, deren erschöpfende Behandlung für die rechnerische Erfassung baispielsweise der Trocknungsvorgänge unerläßlich ist. Zu diesen Fragen gehört der Zusammenhang zwischen Luftzustand und Gutstemperatur während des Trocknens bei bestimmten Arten der Gasströmung. Im folgenden werden diese Verhältnisse untersucht, wobei sich eine gute Übereinstimmung zwischen theoretischen und experimentellen Ergebnissen ergibt.
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    Notes: Die bisherigen Definitionen des Wirkungsgrades von Wärmeaustauschern konnten zwangsläufig nicht in jeder Hinsicht befriedigen. Es wird auch immer schwierig sein, einen Wirkungsgrabegriff auf energetischer Grundlage aufzustellen, solange der Wärmeaustauschapparat allein betrachtet wird, da sich Wärme- und Druckverluste jeweils verschieden auswirken. Daher sollte auch das Arbeitsverfahren, in das der Wärmeaustauscher eingeschaltet ist, mit in Betracht gezogen werden. Im folgenden wird gezeigt, daß sich dann ein auf energetischer Grundlage beruhender Gütegradbegriff schaffen läßt, der zwar von Fall zu Fall neu aufgestellt werden muß, dafür aber eine Reihe von Vorteilen für den Erzeuger und den Abnehmer von Wäreaustauschapparaten bietet.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 103-105 
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    Notes: Der Auslaufbecher DIN 53211 ist ein einfaches, praktisch leicht zu handhabendes Betriebs-Gerät zur Beurteilung der Konsistenz besonders von Farben und Lacken. Die vorliegende Untersuchung zeigt, innerhalb welcher Grenzen der Auslaufbecher tatsächlich geeignet ist, ein zuverlässiges Maß für die Konsistenz mit ihren Nebenerscheinungen, z. B. für die Viskosität usw., zu sein. Der experimentelle Zusammenhang zwischen Auslaufzeit und Viskosität wird durch Versuche mit 11 Normalflüssigkeiten ermittelt. Die genaue Analyse der Versuchsergebnisse gibt einen interessanten Einblick in die Strömungsvorgänge bei diesem Gerät.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 100-102 
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    Notes: Die Aufzeichnung polarographischer Kurven in Tintenschrift gestattet einfachstes Modellieren und Auswerten der Kurven. Für den Betrieb normaler Tintenschreiber unter Verstärkung der Elektrodenströme mittels Verstärker in Saugschaltung1 wurde während des Krieges ein vollelektrisch arbeitendes Zusatzgerät durchgebildet, in dem alle erforderlichen Schaltelemente und Verstellorgane zur Kurvenaufnahme untergebracht sind. Die einfach zu bedienende, robuste und universell verwendbare polarographische Meßeinrichtung läßt sich auch in technischen Betrieben zur Durchführung von Serienanalysen verwenden. Seine Wirkungsweise wird im folgenden unter Beifügung einiger charakteristischer Kurven erläutert.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 110-114 
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    Notes: Vielen Betrieben steht Kühlwasser zur Verfügung, das reich an Carbonathärte ist und daher leicht Versteinungen der Leitungen hervorruft. Um diese Steinbildung zu verhindern, hat sich der Zusatz geringer Mengen an Natriumhexametaphosphat bewährt. Während man zur Prüfung der Brauchbarkeit von Zusätzen bisher einfache Becherglasversuche angestellt hat, haben die Verfasser ein geeignetes, im Laboratorium durchführbares Prüfverfahren entwickelt, wobei die wesentlichen betrieblichen Faktoren berücksichtigt werden können. Im folgenden wird diese Apparatur beschrieben und dann werden damit erzielte Versuchsergebnisse mitgeteilt, die mit den in der Praxis gemachten Erfahrungen gut übereinstimmen. In einem Anhang wird schließlich über Becherglasversuche mit organischen Zusätzen berichtet.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 116-116 
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