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  • AERODYNAMICS  (6)
  • Aeronautics (General)  (3)
  • Cybernetics, Artificial Intelligence and Robotics; Computer Programming and Software; Air Transportation and Safety  (1)
  • 1
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    Transonic and supersonic Euler computations of vortex-dominated flow fields about a generic fighter (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flow fields about a generic flighter model were computed using FL057, a 3-D, finite volume Euler code. Computed pressure coefficients, forces, and moments at several Mach numbers (0.6, 0.8, 1.2, 1.4, and 1.6) are compared with wind tunnel data over a wide range of angles of attack in order to determine the applicability of the code for the analysis of fighter configurations. Two configurations were studied, a wing-body and a wing-body-chine. FL057 predicted pressure distributions, forces, and moments well at low angles of attack, at which the flow was fully attached. The FL057 predictions were also accurate for some test conditions once the leading edge vortex became well established. At the subsonic speeds, FL057 predicted vortex breakdown earlier than that seen in the experimental results. Placing the chine on the forebody delayed the onset of bursting and improved the correlation between numerical and experimental data at the subsonic conditions.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3156 , A-90161 , NAS 1.60:3156
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    3D automatic Cartesian grid generation for Euler flows (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: We describe a Cartesian grid strategy for the study of three dimensional inviscid flows about arbitrary geometries that uses both conventional and CAD/CAM surface geometry databases. Initial applications of the technique are presented. The elimination of the body-fitted constraint allows the grid generation process to be automated, significantly reducing the time and effort required to develop suitable computational grids for inviscid flowfield simulations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3386 , In: AIAA Computational Fluid Dynamics Conference, 11th, Orlando, FL, July 6-9, 1993, Technical Papers. Pt. 2 (A93-44994 18-34); p. 959-969.
    Format: text
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  • 3
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    Unstructured Euler flow solutions using hexahedral cell refinement (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An attempt is made to extend grid refinement into three dimensions by using unstructured hexahedral grids. The flow solver is developed using the TIGER (topologically Independent Grid, Euler Refinement) as the starting point. The program uses an unstructured hexahedral mesh and a modified version of the Jameson four-stage, finite-volume Runge-Kutta algorithm for integration of the Euler equations. The unstructured mesh allows for local refinement appropriate for each freestream condition, thereby concentrating mesh cells in the regions of greatest interest. This increases the computational efficiency because the refinement is not required to extend throughout the entire flow field.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0637
    Format: text
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  • 4
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    An integrated CFD/experimental analysis of aerodynamic forces and moments (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic analysis using computational fluid dynamics (CFD) is most fruitful when it is combined with a thorough program of wind tunnel testing. The understanding of aerodynamic phenomena is enhanced by the synergistic use of both analysis methods. A technique is described for an integrated approach to determining the forces and moments acting on a wind tunnel model by using a combination of experimentally measured pressures and CFD predictions. The CFD code used was FLO57 (an Euler solver) and the wind tunnel model was a heavily instrumented delta wing with 62.5 deg of leading-edge sweep. A thorough comparison of the CFD results and the experimental data is presented for surface pressure distributions and longitudinal forces and moments. The experimental pressures were also integrated over the surface of the model and the resulting forces and moments are compared to the CFD and wind tunnel results. The accurate determination of various drag increments via the combined use of the CFD and experimental pressures is presented in detail.
    Keywords: AERODYNAMICS
    Type: NASA-TM-102195 , A-89145 , NAS 1.15:102195
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  • 5
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    A transonic/supersonic CFD analysis of a generic fighter (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Flow fields about a generic fighter model have been computed using FLO57, a three-dimensional, finite-volume Euler code. Computed pressure coefficients, forces, and moments at several Mach numbers - 0.6, 0.8, 1.2, 1.4, and 1.6 - are compared with wind tunnel data over a wide range of angles of attack in order to determine the applicability of the code for the analysis of fighter configurations. Two configurations were studied, a wing/body and a wing/body/chine. FLO57 predicted pressure distributions, forces, and moments well at low angles of attack, at which the flow was fully attached. The FLO57 predictions were also accurate for some test conditions once the leading-edge vortex became well established. At the subsonic speeds, FLO57 predicted vortex breakdown earlier than that seen in the experimental results. Placing the chine on the forebody delayed the onset of bursting and improved the correlation between numerical and experimental data at the subsonic conditions.
    Keywords: AERODYNAMICS
    Type: ICAS Congress; Sept. 9-14, 1990; Stockholm; Sweden
    Format: text
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  • 6
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    Airships 101: Rediscovering the Potential of Lighter-Than-Air (LTA) (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An overview of airships past, present, and future is provided in a Powerpoint-formatted presentation. This presentation was requested for transfer to the British MOD by Paul Espinosa of NASA Ames, Code PX. The presentation provides general information about airships divided into four main categories: the legacy of NASA Ames in LTA (Lighter-Than-Air), LTA taxonomy and theory, LTA revival and missions, and LTA research and technology.
    Keywords: Aeronautics (General)
    Type: ARC-E-DAA-TN4810
    Format: application/pdf
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  • 7
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    3D Euler flow solutions using unstructured Cartesian and prismatic grids (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A hyperbolic prismatic grid generation technique is combined with a background Cartesian grid for the study of inviscid three-dimensional flows. The mathematics of the hyperbolic prismatic grid generation algorithm are described, and some simple inviscid demonstration cases are presented. By combining the simplicity of the Cartesian background grid with the geometric flexibility and computational efficiencies inherent to prismatic grids, this approach shows promise for improving computational aerodynamic simulations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0331 , ; 12 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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  • 8
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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
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  • 9
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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
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    NASA TECHNICAL REPORTS
  • 10
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    Manned Versus Unmanned Risk and Complexity Considerations for Future Midsized X-Planes (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    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: NASA/TM-2017-219541 , AFRC-E-DAA-TN44856
    Format: application/pdf
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