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  • 1
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    Transient induced drag (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: In the present treatment of the calculation of forces on a wing that is suddenly brought into motion at a constant speed, attention is given to the unsteady potential's contribution to the force balance. Total bound vorticity is produced at the initial impulse. The results obtained are independent of wing aspect ratio; as time increases, this effect on the drag force becomes smaller as the vortex emanating from the trailing edge is left behind. The second contributor to induced drag is the spanwise vorticity shedding that results from the spanwise load distribution of three-dimensional wings. This contribution grows with time as the length of the wake grows.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1203-120
    Format: text
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  • 2
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    A discrete vortex method for the non-steady separated flow over an airfoil (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A discrete vortex method was used to analyze the separated non-steady flow about a cambered airfoil. The foil flow modelling is based on the thin lifting-surface approach, where the chordwise location of the separation point is assumed to be known from experiments or flow-visualization data. Calculated results provided good agreement when compared with the post-stall aerodynamic data of two airfoils. Those airfoil sections differed in the extent of travel of the separation point with increasing angle of attack. Furthermore, the periodic wake shedding was analyzed and its time-dependent influence on the airfoil was investigated.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 102; Jan. 198
    Format: text
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  • 3
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    Modeling aerodynamic responses to aircraft maneuvers - A numerical validation (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 19-25
    Format: text
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  • 4
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    Application of CFD techniques toward the validation of nonlinear aerodynamic models (1985)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Applications of computational fluid dynamics (CFD) methods to determine the regimes of applicability of nonlinear models describing the unsteady aerodynamic responses to aircraft flight motions are described. The potential advantages of computational methods over experimental methods are discussed and the concepts underlying mathematical modeling are reviewed. The economic and conceptual advantages of the modeling procedure over coupled, simultaneous solutions of the gas dynamic equations and the vehicle's kinematic equations of motion are discussed. The modeling approach, when valid, eliminates the need for costly repetitive computation of flow field solutions. For the test cases considered, the aerodynamic modeling approach is shown to be valid.
    Keywords: AERODYNAMICS
    Type: AGARD Unsteady Aerodynamics-Fundamentals and Applications to Aircraft Dynamics; 15 p
    Format: text
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  • 5
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    Evaluation of an aerodynamic-load prediction method on a STOL fighter configuration (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A three-dimensional panel method was used to compute the aerodynamic loads on a large-scale, powered wind tunnel model. The size of the computation grid was selected such that turnaround times, on present computers remained satisfactory. With this constraint, the STOL aircraft configuration was modeled and the capabilities and limitations of the prediction method were investigated. After this study, a similar numerical model was established for a forward-swept-wing aircraft configuration which is planned for large-scale, low-speed testing. The resulting aerodynamic-load predictions are discussed and will be utilized, together with the future experimental results, to obtain a broader validation of this method as well as to reduce the necessary size of the matrix of the test parameters.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0590
    Format: text
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  • 6
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    Linguistics (1964)
    In:  Other Sources
    Details
    Publication Date: 2019-05-21
    Description: Phonology, morphology, syntax, language learning & disturbances, linguistic change, semantics, and logical foundations of language theory
    Keywords: AERODYNAMICS
    Format: text
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  • 7
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    Evaluation of an aerodynamic-load prediction method on a STOL fighter configuration (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A three-dimensional panel method was used to compute the aerodynamic loads on a large-scale, powered wind tunnel model. The size of the computation grid was selected such that turnaround times, on present computers remained satisfactory. With this constraint, the STOL aircraft configuration was modeled and the capabilities and limitations of the prediction method were investigated. After this study, a similar numerical model was established for a forward-swept-wing aircraft configuration which is planned for large-scale, low-speed testing. The resulting aerodynamic-load predictions are discussed and will be utilized, together with the future experimental results, to obtain a broader validation of this method as well as to reduce the necessary size of the matrix of the test parameters.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86782 , REPT-85358 , NAS 1.15:86782
    Format: application/pdf
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  • 8
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    Full-scale aerodynamic characteristics of a propellar installed on a small twin-engine aircraft wing panel (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Full-scale measurements of shaft thrust and torque were made. Wind-tunnel speeds and blade angles were set for full-scale flight conditions. Excellent quality measurements were obtained of the thrust coefficient, the power coefficient, and the propeller efficiency for various values of the advance ratio and the blade incidence angle at 3/4-blade radius. A conventional propeller theory found in the literature was applied to the present results. Although thrust, power, and efficiency were somewhat overpredicted, the advance ratio for maximum efficiency was predicted quite accurately. It was found that, for some conditions, spinner drag could be significant. A simple correction that was based on the spinner base pressure substantially accounted for the changes in efficiency that resulted from this cause.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81285 , A-8478
    Format: application/pdf
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  • 9
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    Lateral aerodynamics of delta wings with leading-edge separation (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 19, p. 2972, Accession no. A82-39142
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 22; 323-328
    Format: text
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  • 10
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    Study of cooling air inlet and exit geometries for horizontally opposed piston aircraft engines (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A semispan wing and nacelle of a typical general aviation twin-engine aircraft was tested to evaluate the cooling capability and drag of several nacelle shapes; the nacelle shapes included cooling air inlet and exit variations. The tests were conducted in the Ames Research Center's 40- by 80-Foot Wind Tunnel. It was found that the cooling air inlet geometry of opposed piston engine installations has a major effect on inlet pressure recovery, but only a minor effect on drag. Exit location showed a large effect on drag, especially for those locations on the sides of the nacelle where the suction characteristics were based on interaction with the wing surface pressures.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1242 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
    Format: text
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