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  • Aircraft Design, Testing and Performance
  • 2015-2019  (287)
  • 1970-1974  (5)
  • 1950-1954  (68)
  • 1945-1949  (168)
  • 1
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    Future Vertical Lift Propulsion Systems & Associated S&T Challenges (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-22
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: GRC-E-DAA-TN74511 , Propulsion and Power Technical Meeting; Oct 29, 2019 - Oct 30, 2019; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    CAMIEM: Compact Additively Manufactured Innovative Electric Motor (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-21
    Description: New manufacturing methods are needed to obtain innovative electric motor designs that have much higher power densities and/or efficiencies compared to the current state-of-the-art. Additive manufacturing offers the potential to radically change motor designs so that they have compact designs, multi-material components, innovative cooling, and optimally designed and manufactured components. New component designs enabled by additive manufacturing technologies have been designed and were fabricated to include the housing, rotors, stator cooling ring, a direct printed stator, and a wire embedded stator. The new components were integrated into the motor and tested evaluate the performance gains in comparison to the baseline electric motor configuration. Partners on the sub-project include NASA GRC, NASA LaRC, NASA AFRC, LaunchPoint Technologies, and the University of Texas El Paso.
    Keywords: Aircraft Design, Testing and Performance
    Type: GRC-E-DAA-TN74521 , Convergent Aeronautics Solutions (CAS) Showcase ; Nov 13, 2019 - Nov 14, 2019; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    An Innovative Feedback Controls Design Approach for Aero Engines (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-18
    Description: The paper describes a feedback controls design approach for a generic regional jet turbofan engine, which can be adapted to aero engines in general. To demonstrate this approach, linear models for control design are generated at different operating conditions from a full envelope nonlinear simulation created with the NASA Glenn Research Center-developed Toolbox for the Modeling and Analysis of Thermodynamic Systems. The primary objective is to design a single feedback controller that achieves good performance, without the need of developing scheduled control designs to cover the engine operating envelope. An additional objective is to progressively design more robust controllers that can perform under large variations in plant dynamics to also cover control for engine limits and potentially for some off nominal or even damaged conditions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2019-220361 , E-19750 , GRC-E-DAA-TN73199 , Propulsion and Energy Forum; Aug 19, 2019 - Aug 22, 2019; Indianapolis, IN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Optimizing the Model of the Viking-400 UAS (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-17
    Description: This project intends to update and redesign imperfections in the scanned 3D CAD model of the Viking 400 aircraft. This aircraft, similar to the Sierra-B UAS, will carry payloads of scientific instruments for research purposes. The goals of this project are to modify the current scanned model such that it better represents the physical qualities of the aircraft, as well as creating the features that are missing from the model. As the model was imported from a different software, many of the critical surfaces did not accurately reflect the actual aircraft. Those parts of the model were redesigned entirely so that they can be edited for future use, as well as correctly representing the aircraft as it is now. Additionally, parts of the aircraft that did not appear in the scanned model were designed and added to the new model. In order to prioritize ease of use for future missions, the model has been reorganized in a logical fashion that enables modification of specific parts of the aircraft. The organization of this model imitates the drawing tree of the Sierra-B, with the intention of maintaining a functional system of redesign, analysis, and implementation. Ultimately, this project will be a catalyst for making Viking 400 into a functional aircraft and increasing scientific research in airborne vehicles.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN70779 , Ames Intern Poster Session; Aug 08, 2019; Moffett Field, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Over-the-Rotor Liner Investigation via the NASA Langley Normal Incidence Tube (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-10
    Description: NASA Langley and Glenn Research Centers have collaborated on the usage of acoustic liners mounted very near or directly over the rotor of turbofan aircraft engines. This collaboration began over a decade ago with the investigation of a metallic foam liner. Similar to conventional acoustic liner applications, this liner was designed to absorb sound generated by the rotor-alone and rotor-stator interaction sources within the fan duct. Given its proximity to the rotor tips, the expectation was that the liner would also serve as a pressure release and thereby inhibit the amount of noise generated. Initial acoustic results were promising, but there was concern regarding potential aerodynamic penalties. Nevertheless, there were sufficient positive results to warrant further investigation. To that end, the current report presents results obtained in the NASA Langley Normal Incidence Tube for 20 acoustic liner candidates for the OTR application. The majority contain grooves at their surface, designed to minimize aerodynamic penalties caused by placing the liner in close proximity to the fan rotor tips. The intent is to assess the acoustic properties of each liner configuration, and in particular to assess the effects of including the grooves on the overall acoustic performance. An additional intent of this paper is to provide documentation regarding recent enhancements to the NASA Langley Normal Incidence Tube.
    Keywords: Aircraft Design, Testing and Performance
    Type: NF1676L-35060 , NASA/TM–2019–220430
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    HyTES Recent Campaigns and Transition to High Altitude Platform (2016)
    In:  Other Sources
    Details
    Publication Date: 2020-01-01
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: JPL-CL-16-2564 , Earth Science Technology Forum; Jun 14, 2019 - Jun 16, 2019; Annapolis, MD; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Radio Occultation Retrieval Using Phase Matching and Optimization (2016)
    In:  Other Sources
    Details
    Publication Date: 2019-12-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: JPL-CL-16-2510 , ROHP-PAZ Technical Meeting; Jun 15, 2016; Barcelona; Spain
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Static and Dynamic Testing of Blunt Bodies in a Subsonic Magnetic Suspension Wind Tunnel (2018)
    In:  CASI
    Details
    Publication Date: 2019-12-24
    Description: The MIT 6-inch magnetic suspension wind tunnel is used in two configurations to measure lift forces of two blunt bodies and produce free-to-pitch oscillations driven by capsule static stability and dynamic instabilities. Lift tests show that static aerodynamic data can be measured on a magnetically levitated model without moment control. Free-to- oscillate results show that magnetic suspension balance system (MSBS) can produce capsule dynamics suitable for extracting static and dynamic stability data.
    Keywords: Aircraft Design, Testing and Performance
    Type: NF1676L-30952 , International Conference on Flow Dynamics; Nov 07, 2018 - Nov 09, 2018; Sendai; Japan
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Using CFD to Develop NASA's X-57 Maxwell Flight Simulator (2019)
    In:  CASI
    Details
    Publication Date: 2019-12-21
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN75498 , International Conference for High Performance Computing, Networking, Storage, and Analysis (SC19); Nov 17, 2019 - Nov 22, 2019; Denver, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Effect of Mass Transfer on Aeroheating in Hypersonic Chemically Reacting Boundary Layers (2019)
    In:  CASI
    Details
    Publication Date: 2019-12-17
    Description: Heat flux characterization of high-enthalpy boundary layer flows is key to optimize the performance and design of Thermal Protection System of next generation aerospace vehicles [1]. At atmospheric entry hypersonic speeds, ablation as well as surface catalycity impact boundary layer aeroheating. Out-gassing occurring from an ablative surface in planetary entry environment introduces a rich set of problems in thermodynamic, fluid dynamic, and material pyrolysis. Ablation leads to out-gassing and surface roughness, both of which are known to affect surface heating in hypersonic chemically reacting boundary layers via three main routes: gas blowing into the boundary layer from the wall, changing the surface heat transfer due to wall-flow chemical reactions, and modifying surface roughness via ablative processes.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN76132 , American Physical Society's Division of Fluid Dynamics Annual Meeting; Nov 23, 2019 - Nov 26, 2019; Seattle, WA; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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