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  • 1995-1999  (2)
  • 1985-1989  (6)
  • 1
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    On the nonlinear aerodynamic and stability characteristics of a generic chine-forebody slender-wing fighter configuration (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An exploratory investigation was conducted of the nonlinear aerodynamic and stability characteristics of a tailless generic fighter configuration featuring a chine-shaped forebody coupled to a slender cropped delta wing in the NASA Langley Research Center's 12-Foot Low-Speed Wind Tunnel. Forebody and wing vortex flow mechanisms were identified through off-body flow visualizations to explain the trends in the longitudinal and lateral-directional characteristics at extreme attitudes (angles of attack and sideslip). The interactions of the vortical motions with centerline and wing-mounted vertical tail surfaces were studied and the flow phenomena were correlated with the configuration forces and moments. Single degree of freedom, free-to-roll tests were used to study the wing rock susceptibility of the generic fighter model. Modifications to the nose region of the chine forebody were examined and fluid mechanisms were established to account for their ineffectiveness in modulating the highly interactive forebody and wing vortex systems.
    Keywords: AERODYNAMICS
    Type: NASA-TM-89447 , A-87174 , NAS 1.15:89447
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Water facilities in retrospect and prospect: An illuminating tool for vehicle design (1987)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Water facilities play a fundamental role in the design of air, ground, and marine vehicles by providing a qualitative, and sometimes quantitative, description of complex flow phenomena. Water tunnels, channels, and tow tanks used as flow-diagnostic tools have experienced a renaissance in recent years in response to the increased complexity of designs suitable for advanced technology vehicles. These vehicles are frequently characterized by large regions of steady and unsteady 3-D flow separation and ensuing vortical flows. The visualization and interpretation of the complicated fluid motions about isolated vehicle components and complete configurations in a time and cost effective manner in hydrodynamic test facilities is a key element in the development of flow control concepts, and, hence, improved vehicle designs. A historical perspective of the role of water facilities in the vehicle design process is presented. The application of water facilities to specific aerodynamic and hydrodynamic flow problems is discussed, and the strengths and limitations of these important experimental tools are emphasized.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AGARD, Aerodynamic and Related Hydrodynamic Studies Using Water Facilities; 28 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    On the nonlinear aerodynamic and stability characteristics of a generic chine-forebody slender-wing fighter configuration (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An exploratory investigation was conducted of the nonlinear aerodynamic and stability characteristics of a tailless generic fighter configuration featuring a chine-shaped forebody coupled to a slender cropped delta wing in the NASA Langley Research Center's 12-Foot Low-Speed Wind Tunnel. Forebody and wing vortex flow mechanisms were identified through off-body flow visualizations to explain the trends in the longitudinal and lateral-directional characteristics at extreme attitudes (angles of attack and sideslip). The interactins of the vortical motions with centerline and wing-mounted vertical tail surfaces were studied and the flow phenomena were correlated with the configuration forces and moments. Single degree-of-freedom, free-to-roll tests were used to study the wing rock susceptibility of the generic fighter model. Modifications to the nose region of the chine forebody were examined and fluid mechanisms were established to account for their ineffectiveness in modulating the highly interactive forebody and wing vortex systems.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-2617
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental study of the vortex flow behavior on a generic fighter wing at subsonic and transonic speeds (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A subsonic and transonic investigation of the vortex flow behavior of a generic fighter configuration with 55-deg cropped delta wing has been conducted in order to improve current understanding of vortical motions on a wing with deflected leading edge flap at moderate and high angles-of-attack. The leading edge vortex strength was reduced, and the vortex was flatter and closer to the wing surface, as the Mach number increased. Transonically, at high angles-of-attack, the test data suggested the development of a cross-flow shock wave above the vortex sheet which coexisted with a rear shock wave. Subsonically, a deflected leading edge flap was able to sustain a concentrated vortex on the forward-facing surface.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-1262
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    On the structure, interaction, and breakdown characteristics of slender wing vortices at subsonic, transonic, and supersonic speeds (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Slender wing vortex flows at subsonic, transonic, and supersonic speeds were investigated in a 6 x 6 ft wind tunnel. Test data obtained include off-body and surface flow visualizations, wing upper surface static pressure distributions, and six-component forces and moments. The results reveal the transition from the low-speed classical vortex regime to the transonic regime, beginning at a freestream Mach number of 0.60, where vortices coexist with shock waves. It is shown that the onset of core breakdown and the progression of core breakdown with the angle of attack were sensitive to the Mach number, and that the shock effects at transonic speeds were reduced by the interaction of the wing and the lead-edge extension (LEX) vortices. The vortex strengths and direct interaction of the wing and LEX cores (cores wrapping around each other) were found to diminish at transonic and supersonic speeds.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-3345
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Overview of HATP Experimental Aerodynamics Data for the Baseline F/A-18 Configuration (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Determining the baseline aerodynamics of the F/A-18 was one of the major objectives of the High-Angle-of-Attack Technology Program (HATP). This paper will review the key data bases that have contributed to our knowledge of the baseline aerodynamics and the improvements in test techniques that have resulted from the experimental program. Photographs are given highlighting the forebody and leading-edge-extension (LEX) vortices. Other data representing the impact of Mach and Reynolds numbers on the forebody and LEX vortices will also be detailed. The level of agreement between different tunnels and between tunnels and flight will be illustrated using pressures, forces, and moments measured on a 0.06-scale model tested in the Langley 7- by 10-Foot High Speed Tunnel, a 0.16-scale model in the Langley 30- by 60-Foot Tunnel, a full-scale vehicle in the Ames 80- by 120-Foot Wind Tunnel, and the flight F/A-18 High Alpha Research Vehicle (HARV). Next, creative use of wind tunnel resources that accelerated the validation of the computational fluid dynamics (CFD) codes will be described. Lastly, lessons learned, deliverables, and program conclusions are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-112360 , NAS 1.15:112360 , High-Angle-of-Attack Technology; Sep 17, 1996 - Sep 19, 1996; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Experimental investigation of the F/A-18 vortex flows at subsonic through transonic speeds (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A subsonic-to-transonic speed wind tunnel study has been conducted to deepen understanding of the nature and possibilities for control of vortical flows associated with wing leading edge extensions (LEXs) on the F/A-18 aircraft; these vortical phenomena encompass vortex breakdown and vortex interactions with vertical stabilizers. Wind tunnel results were correlated with in-flight flow visualizations as well as handling-qualities trend data from a USN F-18 with LEX fences to improve the vertical tail buffet environment. Attention is given to the sensitivity of the vortex flows to Re and Mach numbers, reduced vertical tail excitation due to the presence of a LEX fence, and the interpretation of off-body flow visualizations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-2222 , AIAA Applied Aerodynamics Conference; Jul 31, 1989 - Aug 02, 1989; Seattle, WA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Evaluation of Gritting Strategies for High Angle of Attack Using Wind Tunnel and Flight Test Data for the F/A-18 (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A subsonic study of high-angle-of-attack gritting strategies was undertaken with a 0.06-scale model of the F/A-18, which was assumed to be typical of airplanes with smooth-sided forebodies. This study was conducted in the Langley 7- by 10-Foot High-Speed Tunnel and was intended to more accurately simulate flight boundary layer characteristics on the model in the wind tunnel than would be possible by using classical, low-angle-of-attack gritting on the fuselage. Six-component force and moment data were taken with an internally mounted strain-gauge balance, while pressure data were acquired by using electronically scanned pressure transducers. Data were taken at zero sideslip over an angle-of-attack range from 0 deg to 40 deg and, at selected angles of attack, over sideslip angles from -10 deg to 10 deg. Free-stream Mach number was fixed at 0.30, which resulted in a Reynolds number, based on mean aerodynamic chord, of 1.4 x 10(exp 6). Pressure data measured over the forebody and leading-edge extensions are compared to similar pressure data taken by a related NASA flight research program by using a specially instrumented F/A-18, the High-Alpha Research Vehicle (HARV). Preliminary guidelines for high-angle-of-attack gritting strategies are given.
    Keywords: Aerodynamics
    Type: NASA/TP-1998-207670 , NAS 1.60.207670 , L-17562
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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