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  • Other Sources  (966)
  • AERODYNAMICS  (966)
  • 2000-2004
  • 1990-1994  (578)
  • 1970-1974  (216)
  • 1965-1969  (172)
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  • Other Sources  (966)
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  • 1
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    Navier-Stokes predictions for the F-18 wing and fuselage at large incidence (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 4, Ju; 565-574
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Computational analysis of forebody tangential slot blowing (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An overview of the computational effort to analyze forebody tangential slot blowing is presented. Tangential slot blowing generates side force and yawing moment which may be used to control an aircraft flying at high-angle-of-attack. Two different geometries are used in the analysis: (1) The High Alpha Research Vehicle; and (2) a generic chined forebody. Computations using the isolated F/A-18 forebody are obtained at full-scale wind tunnel test conditions for direct comparison with available experimental data. The effects of over- and under-blowing on force and moment production are analyzed. Time-accurate solutions using the isolated forebody are obtained to study the force onset timelag of tangential slot blowing. Computations using the generic chined forebody are obtained at experimental wind tunnel conditions, and the results compared with available experimental data. This computational analysis compliments the experimental results and provides a detailed understanding of the effects of tangential slot blowing on the flow field about simple and complex geometries.
    Keywords: AERODYNAMICS
    Type: NASA. Dryden Flight Research Center, Fourth High Alpha Conference, Volume 3; 22 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Supersonic jet mixing enhancement by vortex generators (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Experiments were conducted to explore the effects of vortex generators, in the form of tabs projecting normally into the jet, on the mixing and the far-field noise characteristics of a jet. A converging-diverging nozzle with a design Mach number of 1.36 was used in the experiments. The flow regimes from subsonic to highly underexpanded supersonic conditions were studied. One, two, and four tabs were used and some of the findings of previous investigators were examined and confirmed. The tabs eliminated screech noise from moderately overexpanded cases to highly underexpanded cases. Detailed flow visualizations and measurements showed that two tabs bifurcated the jet at all Mach numbers. While the effect of two tabs was persistent and the jet remained bifurcated, the distortions produced by one and four tabs disappeared by a streamwise distance of approximately 16 jet diameters. Two and four tabs significantly increased the entrainment of ambient air into the jet.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-2263
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Supersonic jet mixing enhancement by 'delta-tabs' (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The results of a continuing investigation of the effect of vortex generators, in the form of small tabs at the nozzle exit, on the evolution of a jet are reported. Primarily, tabs of triangular shape are considered, and the effect is studied up to an equivalent jet Mach number of 1.8. By changing the orientation of the tab with respect to the nozzle exit plane, streamwise vortex pairs of opposite sign were generated. This resulted in either an outward selection of jet core fluid into the ambient or an inward indentation of the mixing layer into the core of the jet. A triangular shaped tab with its apex leaning downstream, referred to as a delta tab, was found to be the most effective in influencing the jet evolution. Two delta tabs, spaced 180 degrees apart, completely bifurcated the jet. Four delta tabs increased jet mixing substantially, more than by various other methods tried previously; the mass flux at fourteen jet diameters downstream from the nozzle increased by about 50 percent over that for the no tab case. The tabs were found to be effective in jets with laminar or turbulent boundary layers as well as in jets with low or high core turbulence intensities.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-3548
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Navier-Stokes predictions of the flowfield around the F-18 (HARV) wing and fuselage at large incidence (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In support of the NASA High Alpha Technology Program, Navier-Stokes solutions have been obtained using the Chimera overset grid scheme for flow over the wing, fuselage, and wing leading-edge extension (LEX) of the F/A-18 High Alpha Research Vehicle (HARV) at high incidence. Solutions are also presented for flow over the fuselage forebody at high angles of attack. The solutions are for turbulent flows at high-Reynolds-number flight-test conditions, and are compared with available qualitative and quantitative experimental data. Comparisons of predicted surface flow patterns, off-surface flow visualization, and surface-pressure distributions are in good agreement with flight-test data. The ability of the numerical method to predict the bursting of the LEX vortex as it encounters the adverse pressure gradient field of the wing is demonstrated, and the capability of predicting high-angle-of-attack aerodynamics around realistic aircraft configurations is established.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0099
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Finite wing aerodynamics with simulated glaze ice (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effect of a simulated glaze ice accretion on the aerodynamic performance of a three-dimensional wing is studied experimentally. The model used for these tests was a semi-span wing of effective aspect ratio five, mounted from the sidewall of the UIUC subsonic wind tunnel. The model has an NACA 0012 airfoil section on a rectangular, untwisted planform with interchangeable leading edges to allow for testing both the baseline and the iced wing geometry. A three-component sidewall balance was used to measure lift, drag and pitching moment on the clean and iced model. A four-beam two-color fiberoptic laser Doppler velocimeter (LDV) was used to map the flowfield along several spanwise cuts on the model. Preliminary results from LDV scans, which will be the bulk of this paper, are presented following the force balance measurement results. Initial comparison of LDV surveys compare favorably with inviscid theory results and 2D split hot-film measurements near the model surface.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0414
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Computational investigation of slot blowing for fuselage forebody flow control (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents a computational investigation of a tangential slot blowing concept for generating lateral control forces on an aircraft fuselage forebody. The effects of varying both the jet width and jet exit velocity for a fixed location slot are analyzed. This work is aimed at aiding researchers in designing future experimental and computational models of tangential slot blowing. The primary influence on the resulting side force of the forebody is seen to be the jet mass flow rate. This influence is sensitive to different combinations of slot widths and jet velocities over the range of variables considered. Both an actuator plane and an overset grid technique are used to model the tangential slot. The overset method successfully resolves the details of the actual slot geometry, extending the generality of the numerical method. The actuator plane concept predicts side forces similar to those produced by resolving the actual slot geometry.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0020
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Numerical simulation of high-incidence flow over the F-18 aircraft (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Navier-Stokes solutions have been obtained using the Chimera overset grid scheme for flow over the wing, fuselage, and wing leading-edge extension (LEX) of the F-18 aircraft at high incidence. Solutions are also presented for flow over the fuselage forebody at high angles of attack. The solutions are for turbulent flows at high-Reynolds number flight-test conditions, and are compared with available qualitative and quantitative experimental data. Comparisons of predicted surface flow patterns, off-surface flow visualizations, and surface-pressure distributions are in good agreement with flight-test data. The ability of the numerical method to predict the bursting of the LEX vortex as it encounters the adverse pressure gradient field of the wing is demonstrated.
    Keywords: AERODYNAMICS
    Type: ICAS Congress; Sept. 9-14, 1990; Stockholm; Sweden
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Prospects for reduced energy transports: A preliminary analysis (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The recent energy crisis and subsequent substantial increase in fuel prices have provided increased incentive to reduce the fuel consumption of civil transport aircraft. At the present time many changes in operational procedures have been introduced to decrease fuel consumption of the existing fleet. In the future, however, it may become desirable or even necessary to introduce new fuel-conservative aircraft designs. This paper reports the results of a preliminary study of new near-term fuel conservative aircraft. A parametric study was made to determine the effects of cruise Mach number and fuel cost on the optimum configuration characteristics and on economic performance. For each design, the wing geometry was optimized to give maximum return on investment at a particular fuel cost. Based on the results of the parametric study, a nominal reduced energy configuration was selected. Compared with existing transport designs, the reduced energy design has a higher aspect ratio wing with lower sweep, and cruises at a lower Mach number. It has about 30% less fuel consumption on a seat-mile basis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62383
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Supersonic jet mixing enhancement by delta-tabs (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of a continuing investigation of the effect of vortex generators, in the form of small tabs at the nozzle exit, on the evolution of a jet are reported. Primarily, tabs of triangular shape are considered, and the effect is studied up to an equivalent jet Mach number of 1.8. By changing the orientation of the tab with respect to the nozzle exit plane, streamwise vortex pairs of opposite sign were generated. This resulted in either an outward election of jet core fluid into the ambient or an inward indentation of the mixing layer into the core of the jet. A triangular shaped tab with its apex leaning downstream, referred to as a delta tab, was found to be the most effective in influencing the jet evolution. Two delta tabs, spaced 180 degrees apart, completely bifurcated the jet. Four delta tabs increased jet mixing substantially, more than by various other methods tried previously; the mass flux at fourteen jet diameters downstream from the nozzle increased by about 50 percent over that for the no tab case. The tabs were found to be effective in jets with laminar or turbulent boundary layers as well as in jets with low or high core turbulence intensities.
    Keywords: AERODYNAMICS
    Type: NASA-TM-105664 , E-6993 , NAS 1.15:105664 , AIAA PAPER 92-3548 , Joint Propulsion Conference and Exhibit; Jul 06, 1992 - Jul 08, 1992; Nashville, TN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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