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  • 1
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    Hypersonic forebody lift-induced drag (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The dominance of body-like shapes for hypersonic vehicles places emphasis on better understanding of pertinenet body flow physics. Computational methods are implemented to enhance the knowledge of drag components generated by the production of lift forces at hypersonic speeds. Three forebody shapes are examined to identify the effects related to body shape parameters. A Navier-Stokes code and classical Newtonian theory code provide predictions of the polar shapes upon which conclusions are drawn. In particular, it is noted that hypersonic body polar shapes are somewhat irregular; the result of incidence-induced form drag. Test data which supports this finding is identified. The means for reducing hypersonic body lift-induced drag are also identified, along with applied computational schemes that can reduce the cost of a configuration design program.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 892345
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    F-14A aircraft high-speed flow simulations (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A model of the Grumman/Navy F-14A aircraft was developed for analyses using the NASA/Grumman Transonic Wing-Body Code. Computations were performed for isolated wing and wing fuselage glove arrangements to determine the extent of aerodynamic interference effects which propagate outward onto the main wing outer panel. Additional studies were conducted using the full potential analysis, FLO 22, to calibrate any inaccuracies that might accrue because of small disturbance code limitations. Comparisons indicate that the NASA/Grumman code provides excellent flow simulations for the range of wing sweep angles and flow conditions that will be of interest for the upcoming F-14 Variable Sweep Flight Transition Experiment.
    Keywords: AERODYNAMICS
    Type: NASA-CR-172559 , NAS 1.26:172559
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Elements of computational engine-airframe integration (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Computerized flow simulation methods are being developed to refine the traditional engine-airframe integration process. These analyses reduce design risk, minimize wind tunnel and flight test requirements, and provide detailed design information not available by any other means. This paper describes computational tools which have matured sufficiently to permit project applications. Several applications are combined with research studies to illustrate the prediction of high-speed nonlinear phenomena associated with engine inlet flow rate, nacelle shape and position, afterbody shape and integration, propeller slipstream interactions, airframe-induced inlet flow, and pylon integration. Both fighter and transport configurations are used to highlight current capabilities and future requirements.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-0117
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Complex configuration analysis at transonic speeds (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Advanced performance requirements of new combat and transport aircraft together with design time constraints intensify the development and application of three dimensional computational analyses. A computational method which was developed for the specific purpose of providing an engineering analysis of complex aircraft configurations at transonic speeds. Particular attention is given to the recently incorporated wing viscous interaction and canard capabilities. The treatment of fuselage fairings, nacelles, and pylons is reviewed. The means for keeping computing resources at reasonable levels are identified. Three configurations were selected for correlations with experimental data. Taken together, the comparisons illustrate the full extent of current analysis capabilities. The configurations include: (1) a wing fuselage canard fighter; (2) a transport with fuselage fairings, four nacelles, four pylons; and (3) a space vehicle which includes an external fuel tank and rocket boosters (transonic launch configuration).
    Keywords: AERODYNAMICS
    Type: AGARD Subsonic(Transonic Configuration Aerodyn.; 13 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Towards complete configurations using an embedded grid approach (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A new approach to simulating transonic flow about transport configurations is briefly outlined. The methods embedded grid scheme provides a high degree of computational resolution coupled with geometric flexibility for future applications to complex shapes. Calculations presented illustrate aspects of transonic transport design including fuselage design, determination of wing control surface deflection effectiveness, and wing design.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3030
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Transonic Flow Field Analysis for Wing-Fuselage Configurations (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computational method for simulating the aerodynamics of wing-fuselage configurations at transonic speeds is developed. The finite difference scheme is characterized by a multiple embedded mesh system coupled with a modified or extended small disturbance flow equation. This approach permits a high degree of computational resolution in addition to coordinate system flexibility for treating complex realistic aircraft shapes. To augment the analysis method and permit applications to a wide range of practical engineering design problems, an arbitrary fuselage geometry modeling system is incorporated as well as methodology for computing wing viscous effects. Configuration drag is broken down into its friction, wave, and lift induced components. Typical computed results for isolated bodies, isolated wings, and wing-body combinations are presented. The results are correlated with experimental data. A computer code which employs this methodology is described.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3243
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Transonic flow over wing/fuselage configurations (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Wing Body Code (WIBCO) program simulates flow-field configurations for reduction of design cost and improvement of aircraft performance. Inputs to WIBCO consist of ambient flow conditions and geometric configuration data; grid control and relaxation parameters are internally set. Outputs include input data echo, grid system verification, relaxation-solution convergence history, and computed velocities, pressures, forces, moments, reference lengths, and areas. Program is written in FORTRAN IV for batch execution.
    Keywords: MECHANICS
    Type: LAR-12702 , NASA Tech Briefs (ISSN 0145-319X); 5; 4; P. 482
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Simulated transonic flows for aircraft with nacelles, pylons, and winglets (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computational method which simulates transonic flow about wing-fuselage configurations has been extended to include the treatment of multiple body and non-planar wing surfaces. The finite difference relaxation scheme is characterized by a modified small disturbance flow equation and multiple embedded grid system. Wing-body combinations with as many as four nacelles/pods, four pylons, and wing-tip-mounted winglets can be analyzed. A scheme for modeling inlet spillage and engine exhaust interference effects has been included. Computed results are correlated with experimental data for three transport configurations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0130 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Computational transonic flow about realistic aircraft configurations (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A numerical method has been developed to compute transonic flows about realistic wing-fuselage configurations. The finite difference scheme employs an improved small disturbance flow equation. A unique grid embedding technique, which was heretofore applied to airfoils and wings, has been extended to include the treatment of both body and wing-body shapes. The resulting high-density mesh is shown to be a valuable asset in resolving details of the three-dimensional flow. A mathematical modeling system is used to process arbitrary fuselage geometries for body boundary conditions. Correlations with experimental data for simple isolated bodies, an isolated fuselage, and wing-fuselage combinations are included.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-104 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
    Format: text
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