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  • 1
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    Navier-Stokes simulation of a close-coupled canard-wing-body configuration (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 830-838
    Format: text
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  • 2
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    Transonic aeroelasticity of wings with tip stores (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 688-695
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  • 3
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    Transonic aeroelasticity of fighter wings with active control surfaces (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 682-684
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  • 4
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    Effects of modal symmetry on transonic aeroelastic characteristics of wing-body configurations (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 271-280
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  • 5
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    Navier-Stokes simulation of a close-coupled canard-wing-body configuration (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The thin-layer Navier-Stokes equations are solved for the flow about a coplanar close-coupled canard-wing-body configuration at a transonic Mach number of 0.90 and at angles of attack ranging from 0 to 12 degrees. The influence of the canard on the wing flowfield, including canard-wing vortex interaction and wing vortex breakdown, is investigated. A study of canard downwash and canard leading-edge vortex effects, which are the primary mechanisms of the canard-wing interaction, is emphasized. Comparisons between the computations and experimental measurements of surface pressure coefficients, lift, drag and pitching moment data are favorable. A grid refinement study for configurations with and without canard shows that accurate results are obtained using a refined grid for angles of attack where vortex burst is present. At an angle of attack of approximately 12 deg, favorable canard-wing interaction which delays wing vortex breakdown is indicated by the computations and is in good agreement with experimental findings.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0070
    Format: text
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  • 6
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    Transonic aeroelasticity of wings with active control surfaces (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Transonic aeroelasticity of wings with active control surfaces is studied by using the unsteady-small disturbance transonic aerodynamic equations coupled with modal structural equations of motion. The aerodynamic and structural equations of motion are simultaneously integrated by a time-accurate numerical scheme. A procedure of synthesizing active controls with unsteady transonics is presented. Flutter suppression in the transonic regime using active controls is demonstrated for a rectangular wing. Characteristics of a selected control law in the transonic regime are studied. The results from this study are useful in the design of active control systems in the transonic regime.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0709
    Format: text
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  • 7
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    Navier-Stokes Simulation of the Canard-Wing-Body Longitudinal Dynamic Stability Characteristics (1996)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: Many modern aircraft are canard-configured for aircraft control and improved aerodynamic performance. Canards can often enhance aircraft cruise performance, maneuverability and agility. For close-coupled canard configurations, the aerodynamic interaction between the canard and wing significantly changes the flow characteristics of the wing. In unsteady flow, such changes in the flow structure and performance of wings can be quite pronounced. Accurate modeling of the unsteady aerodynamics is essential for potential CFD design and analysis of such configurations. A time-accurate numerical simulation is performed to study the unsteady aerodynamic interaction between a canard and wing with emphasis on the effects of the canard on the configuration's dynamic response characteristics. The thin-layer Reynolds-averaged Navier-Stokes Equations with various turbulence models are used in this study. Computations are made on a generic, analytically-defined, close-coupled canard-wing-body configuration which has been the subject of numerous previously published experimental studies during the 1970's to mid-80's. More recently, a series of steady-flow simulations has been performed and published by the author. In the current study, the configuration is given prescribed ramp and oscillatory motions in order to predict characteristics such as the damping-in-pitch and oscillatory longitudinal stability parameters. The current computations are made at high-subsonic and transonic Mach numbers, moderate angles-of- attack from -4 to 20 degrees, and at various pitch rates and reduced frequencies. Comparisons of pressures and integrated force quantities (e.g. lift, drag, pitching moment and selected dynamic parameters) are made with other published computational results and available experimental data. Results showing the unsteady effects of the canard on surface pressures, integrated forces, canard-wing vortex interaction and vortex breakdown will be presented.
    Keywords: Aircraft Stability and Control
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  • 8
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    Role of High-End Computing in Meeting NASA's Science and Engineering Challenges (2006)
    In:  CASI
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    Publication Date: 2019-08-13
    Description: Two years ago, NASA was on the verge of dramatically increasing its HEC capability and capacity. With the 10,240-processor supercomputer, Columbia, now in production for 18 months, HEC has an even greater impact within the Agency and extending to partner institutions. Advanced science and engineering simulations in space exploration, shuttle operations, Earth sciences, and fundamental aeronautics research are occurring on Columbia, demonstrating its ability to accelerate NASA s exploration vision. This talk describes how the integrated production environment fostered at the NASA Advanced Supercomputing (NAS) facility at Ames Research Center is accelerating scientific discovery, achieving parametric analyses of multiple scenarios, and enhancing safety for NASA missions. We focus on Columbia s impact on two key engineering and science disciplines: Aerospace, and Climate. We also discuss future mission challenges and plans for NASA s next-generation HEC environment.
    Keywords: Mathematical and Computer Sciences (General)
    Type: The Fourth International Conference on Computational Fluid Dynamics; Jul 10, 2006 - Jul 14, 2006; Ghent, Belguim; Belgium
    Format: application/pdf
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  • 9
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    Unsteady Transonics of a Wing With Tip Store (1986)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The presence of tip stores influences both the aerodynamic and aeroelastic performances of wings. Such effects are more pronounced in the transonic regime. In this study, a theoretical method is developed, for the first time, to compute unsteady transonics of oscillating wings with tip stores. The method is based on the small-disturbance aerodynamic equations or motion from the potential-flow theory. To validate the method, subsonic and transonic aerodynamic computations are made for a wing of low aspect ratio, and they are compared with the available experimental data. The comparisons are favorable. The strong effects of the tip store on the transonic aerodynamics on the wing are also illustrated. The method developed in this study can be used for transonic aeroelastic computations of wings with tip stores.
    Keywords: Aerodynamics
    Type: AIAA Paper 86-0010 , Journal of Aircraft; 23; 8; 662-668|Aerospace Sciences; Jan 06, 1986 - Jan 09, 1986; Reno, NV; United States
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  • 10
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    A parametric study of supersonic laminar flow for swept wings using linear stability analysis (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A parametric study to predict the extent of laminar flow on the upper surface of a generic swept-back wing (NACA 64A010 airfoil section) at supersonic speeds was conducted. The results were obtained by using surface pressure predictions from an Euler/Navier-Stokes computational fluid dynamics code coupled with a boundary layer code, which predicts detailed boundary layer profiles, and finally with a linear stability code to determine the extent of laminar flow. The parameters addressed are Reynolds number, angle of attack, and leading-edge wing sweep. The results of this study show that an increase in angle of attack, for specific Reynolds numbers, can actually delay transition. Therefore, higher lift capability, caused by the increased angle of attack, as well as a reduction in viscous drag due to the delay in transition is possible for certain flight conditions.
    Keywords: Aerodynamics
    Type: NASA-TM-111258 , NAS 1.15:111258 , AIAA Paper 95-2277 , 26th AIAA Fluid Dynamics Conference; Jun 19, 1995 - Jun 22, 1995; San Diego, CA; United States
    Format: application/pdf
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