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  • 1
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    Variable Geometry Aircraft Wing Supported by Struts And/Or Trusses (2016)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The present invention provides an aircraft having variable airframe geometry for accommodating efficient flight. The aircraft includes an elongated fuselage, an oblique wing pivotally connected with said fuselage, a wing pivoting mechanism connected with said oblique wing and said fuselage, and a brace operably connected between said oblique wing and said fuselage. The present invention also provides an aircraft having an elongated fuselage, an oblique wing pivotally connected with said fuselage, a wing pivoting mechanism connected with said oblique wing and said fuselage, a propulsion system pivotally connected with said oblique wing, and a brace operably connected between said propulsion system and said fuselage.
    Keywords: Aircraft Design, Testing and Performance; Aircraft Stability and Control
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    UAM Research at NASA (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-08
    Description: Presentation for Oshkosh 2019 describing UAM research at NASA
    Keywords: Aeronautics (General); Engineering (General)
    Type: ARC-E-DAA-TN70709 , EAA Airventure 2019; Jul 22, 2019 - Jul 28, 2019; Oshkosh, WI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Estimating Flow-Through Balance Momentum Tares with CFD (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the process used for estimating flow-through balance momentum tares. The interaction of jet engine exhausts on the BOEINGERA Hybrid Wing Body (HWB) was simulated in the NFAC 40x80 wind tunnel at NASA Ames using a pair of turbine powered simulators (TPS). High-pressure air was passed through a flow-through balance and manifold before being delivered to the TPS units. The force and moment tares that result from the internal shear and pressure distribution were estimated using CFD. Validation of the CFD simulations for these complex internal flows is a challenge, given limited experimental data due to the complications of the internal geometry. Two CFD validation efforts are documented, and comparisons with experimental data from the final model installation are provided.
    Keywords: Aircraft Design, Testing and Performance; Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN28731 , AIAA Science and Technology Forum and Exposition (SciTech 2016); Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Safe Autonomous Flight Environment (SAFE50) for the Notional Last 50 ft of Operation of 55 lb Class of UAS (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The most difficult phase of small Unmanned Aerial System (sUAS) deployment is autonomous operations below the notional 50 ft in urban landscapes. Understanding the feasibility of safely flying sUAS autonomously below 50 ft is a game changer for many civilian applications. This paper outlines three areas of research currently underway which address key challenges for flight in the urban landscape. These are: (1) Off-line and On-board wind estimation and accommodation; (2) Real-time trajectory planning via characterization of obstacles using a LIDAR; (3) On-board information fusion for real-time decision-making and safe trajectory generation.
    Keywords: Cybernetics, Artificial Intelligence and Robotics; Computer Programming and Software; Air Transportation and Safety
    Type: ARC-E-DAA-TN38504 , SciTech 2017; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    NASA ERA Integrated CFD for Wind Tunnel Testing of Hybrid Wing-Body Configuration (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASAs Environmentally Responsible Aviation (ERA) Project explores enabling technologies to reduce aviations impact on the environment. One research challenge area for the project has been to study advanced airframe and engine integration concepts to reduce community noise and fuel burn. In order to achieve this, complex wind tunnel experiments at both the NASA Langley Research Centers (LaRC) 14x22 and the Ames Research Centers 40x80 low-speed wind tunnel facilities were conducted on a Boeing Hybrid Wing Body (HWB) configuration. These wind tunnel tests entailed various entries to evaluate the propulsion airframe interference effects including aerodynamic performance and aeroacoustics. In order to assist these tests in producing high quality data with minimal hardware interference, extensive Computational Fluid Dynamic (CFD) simulations were performed for everything from sting design and placement for both the wing body and powered ejector nacelle systems to the placement of aeroacoustic arrays to minimize its impact on the vehicles aerodynamics. This paper will provide a high level summary of the CFD simulations that NASA performed in support of the model integration hardware design as well as some simulation guideline development based on post-test aerodynamic data. In addition, the paper includes details on how multiple CFD codes (OVERFLOW, STAR-CCM+, USM3D, and FUN3D) were efficiently used to provide timely insight into the wind tunnel experimental setup and execution.
    Keywords: Fluid Mechanics and Thermodynamics; Aerodynamics; Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN28678 , AIAA Science and Technology Forum and Exposition 2016; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    NASA ERA Integrated CFD for Wind Tunnel Testing of Hybrid Wing-Body Configuration (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASA Environmentally Responsible Aviation (ERA) Project explored enabling technologies to reduce impact of aviation on the environment. One project research challenge area was the study of advanced airframe and engine integration concepts to reduce community noise and fuel burn. To address this challenge, complex wind tunnel experiments at both the NASA Langley Research Center's (LaRC) 14'x22' and the Ames Research Center's 40'x80' low-speed wind tunnel facilities were conducted on a BOEING Hybrid Wing Body (HWB) configuration. These wind tunnel tests entailed various entries to evaluate the propulsion-airframe interference effects, including aerodynamic performance and aeroacoustics. In order to assist these tests in producing high quality data with minimal hardware interference, extensive Computational Fluid Dynamic (CFD) simulations were performed for everything from sting design and placement for both the wing body and powered ejector nacelle systems to the placement of aeroacoustic arrays to minimize its impact on vehicle aerodynamics. This paper presents a high-level summary of the CFD simulations that NASA performed in support of the model integration hardware design as well as the development of some CFD simulation guidelines based on post-test aerodynamic data. In addition, the paper includes details on how multiple CFD codes (OVERFLOW, STAR-CCM+, USM3D, and FUN3D) were efficiently used to provide timely insight into the wind tunnel experimental setup and execution.
    Keywords: Aircraft Design, Testing and Performance; Numerical Analysis; Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN28326 , AIAA Science and Technology (SciTech) Forum and Exposition 2016; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Manned Versus Unmanned Risk and Complexity Considerations for Future Midsized X-Planes (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objective of this work was to identify and estimate complexity and risks associated with the development and testing of new low-cost medium-scale X-plane aircraft primarily focused on air transport operations. Piloting modes that were evaluated for this task were manned, remotely piloted, and unmanned flight research programs. This analysis was conducted early in the data collection period for X-plane concept vehicles before preliminary designs were complete. Over 50 different aircraft and system topics were used to evaluate the three piloting control modes. Expert group evaluations from a diverse set of pilots, engineers, and other experts at Aeronautics Research Mission Directorate centers within the National Aeronautics and Space Administration provided qualitative reasoning on the many issues surrounding the decisions regarding piloting modes. The group evaluations were numerically rated to evaluate each topic quantitatively and were used to provide independent criteria for vehicle complexity and risk. An Edwards Air Force Base instruction document was identified that emerged as a source of the effects found in our qualitative and quantitative data. The study showed that a manned aircraft was the best choice to align with test activities for transport aircraft flight research from a low-complexity and low-risk perspective. The study concluded that a manned aircraft option would minimize the risk and complexity to improve flight-test efficiency and bound the cost of the flight-test portion of the program. Several key findings and discriminators between the three modes are discussed in detail.
    Keywords: Aeronautics (General)
    Type: AFRC-E-DAA-TN41196 , Aviation 2017; Jun 05, 2017 - Jun 09, 2017; Denver, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    MiniWall Tool for Analyzing CFD and Wind Tunnel Large Data Sets (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: It is challenging to review and assimilate large data sets created by Computational Fluid Dynamics (CFD) simulations and wind tunnel tests. Over the past 10 years, NASA Ames Research Center has developed and refined a software tool dubbed the MiniWall to increase productivity in reviewing and understanding large CFD-generated data sets. Under the recent NASA ERA project, the application of the tool expanded to enable rapid comparison of experimental and computational data. The MiniWall software is browser based so that it runs on any computer or device that can display a web page. It can also be used remotely and securely by using web server software such as the Apache HTTP server. The MiniWall software has recently been rewritten and enhanced to make it even easier for analysts to review large data sets and extract knowledge and understanding from these data sets. This paper describes the MiniWall software and demonstrates how the different features are used to review and assimilate large data sets.
    Keywords: Fluid Mechanics and Thermodynamics; Computer Programming and Software
    Type: ARC-E-DAA-TN38505 , AIAA SciTech Forum 2017; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 9
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    MiniWall Tool for Analyzing CFD and Wind Tunnel Large Data Sets (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: It is challenging to review and assimilate large data sets created by Computational Fluid Dynamics (CFD) simulations and wind tunnel tests. Over the past 10 years, NASA Ames Research Center has developed and refined a software tool dubbed the "MiniWall" to increase productivity in reviewing and understanding large CFDgenerated data sets. Under the recent NASA ERA project, the application of the tool expanded to enable rapid comparison of experimental and computational data. The MiniWall software is browser based so that it runs on any computer or device that can display a web page. It can also be used remotely and securely by using web server software such as the Apache HTTP Server. The MiniWall software has recently been rewritten and enhanced to make it even easier for analysts to review large data sets and extract knowledge and understanding from these data sets. This paper describes the MiniWall software and demonstrates how the different features are used to review and assimilate large data sets.
    Keywords: Computer Programming and Software; Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN37854 , AIAA SciTech Forum 2017; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    VIPER Integrated MDAO Analysis for Conceptual Design of Supersonic X-Plane Vehicles (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A streamlined Multi-Disciplinary Analysis and Optimization (MDAO) process is being developed to provide feedback on conceptual designs and early airspace modeling assessments of unconventional aircraft. This MDAO process has been demonstrated using a Low-Boom Flight Demonstrator (LBFD) like configuration by performing a trade study of various flap sizes. The results of this trade showed that shorter takeoff distances are achieved with increased flap chord and flap deflections. This trend is unlike conventional transport type aircraft which typically show increased required takeoff distances due to the increased drag during its take-off flap configurations. The LBFD like configuration results are attributed to its high engine thrust which overcomes the higher drag associated with these takeoff flap configurations.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM—2019–220239 , ARC-E-DAA-TN59874
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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