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  • 1
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    Calibration and flight results for the Ares I-X 5-hole probe (2011)
    Elsevier
    Details
    Publication Date: 2011-04-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Experimental study of effects of forebody geometry on high angle-of-attack stability (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Aircraft (ISSN 0021-8669); 25; 591-597
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Dynamic stall effects and applications to high performance aircraft (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Recent research conducted at the NASA Langley Research Center on the effects of large amplitude pitching motions on the aerodynamic characteristics of modern fighter aircraft configurations is highlighted. Wind tunnel tests were conducted on simple flat-plate wings to gain understanding of the complex flow phenomena during unsteady motions at high angles of attack. Studies then progressed to a representative modern fighter configuration. Using a computer controlled dynamic apparatus, tests were conducted to investigate effects of pitch rate and motion time history and to determine the persistence of unsteady effects. Data were also obtained in sideslip and with control surface deflections to investigate dynamic effects on lateral stability and available control power. Force and moment data were obtained using a 6-component internal strain-gage balance. To aid in the interpretation of the results, flow visualization using a laser light-sheet system was also obtained. Results of these tests are discussed, along with their implications on the maneuverability of future advanced airplanes designed to operate in the highly dynamic, high angle-of-attack environment.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD, Special Course on Aircraft Dynamics at High Angles of Attack: Experiments and Modelling; 15 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    In-Flight Flow Visualization Results of the F-106B with a Vortex Flap (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-28
    Description: Surface and off-surface flow visualization techniques were used to visualize the three-dimensional vortex flows on the F-106 aircraft with vortex flaps installed. Results at angles of attack between 9 degrees to 18 degrees and Mach numbers from 0.3 to 0.9 are presented. A smoke flow vapor screen technique was used to document leading-edge vortex paths and sizes, while an oil flow technique was employed to provide detailed information on reattachment and separation line locations and other flow details. Results were obtained for two vortex flap deflection angles, 30 degrees and 40 degrees. Flow visualization revealed the existence of a multiple vortex system that had not previously been seen in subscale tests or predicted for this configuration. The vortex flap generated a leading-edge vortex system that reattached near the flap hinge over a wide angle of attack range. In addition to the primary vortex, flow visualization revealed the presence of several distinct vortices which traced a path from the vortex flap and then over the wing.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Symposium on Advanced Flow Management. Part A: Vortex Flows and High Angle of Attack for Military Vehicles. Part B: Heat Transfer and Cooling in Propulsion and Power Systems; RTO-MP-069(I)-Pt-A-B
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Application of Wind Tunnel Free-Flight Technique for Wake Vortex Encounters (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel investigation was conducted in the Langley 30- by 60-Foot Tunnel to assess the free-flight test technique as a tool in research on wake vortex encounters. A typical 17.5-percent scale business-class jet airplane model was flown behind a stationary wing mounted in the forward portion of the wind tunnel test section. The span ratio (model span-generating wingspan) was 0.75. The wing angle of attack could be adjusted to produce a vortex of desired strength. The test airplane model was successfully flown in the vortex and through the vortex for a range of vortex strengths. Data obtained included the model airplane body axis accelerations, angular rates, attitudes, and control positions as a function of vortex strength and relative position. Pilot comments and video records were also recorded during the vortex encounters.
    Keywords: Aircraft Stability and Control
    Type: NASA-TP-3672 , NAS 1.60:3672 , L-17462
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Piloted-simulation study of effects of vortex flaps on low-speed handling qualities of a Delta-wing airplane (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A piloted-simulation study was conducted to investigate the effects of vortex flaps on low-speed handling qualities of a delta-wing airplane. The simulation math model was developed from wind tunnel tests of a 0.15 scale model of the F-106B airplane. Pilot evaluations were conducted using a six-degree-of-freedom motion base simulator. The results of the investigation showed that the reduced static longitudinal stability caused by the vortex flaps significantly degraded handling qualities in the approach-to-landing task. Acceptable handling qualities could be achieved by limiting the aft center-of-gravity location, consequently reducing the operational envelope of the airplane. Further improvement were possible by modifying the flight control force-feel system to reduce pitch-control sensitivity.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2747 , L-16307 , NAS 1.60:2747
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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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
  • 8
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    Unsteady aerodynamic characteristics of a fighter model undergoing large-amplitude pitching motions at high angles of attack (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effects of harmonic or constant-rate-ramp pitching motions (giving angles of attack from 0 to 75 deg) on the aerodynamic performance of a fighter-aircraft model with highly swept leading-edge extensions are investigated experimentally in the NASA Langley 12-ft low-speed wind tunnel. The model configuration and experimental setup are described, and the results of force and moment measurements and flow visualizations are presented graphically and discussed in detail. Large force overshoots and hysteresis are observed and attributed to lags in vortical-flow development and breakup. The motion variables have a strong influence on the persistence of dynamic effects, which are found to affect pitch-rate capability more than flight-path turning performance.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0309
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Piloted simulation study of an ILS approach of a twin-pusher business/commuter turboprop aircraft configuration (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A six-degree-of-freedom nonlinear simulation of a twin-pusher, turboprop business/commuter aircraft configuration representative of the Cessna ATPTB (Advanced turboprop test bed) was developed for use in piloted studies with the Langley General Aviation Simulator. The math models developed are provided, simulation predictions are compared with with Cessna flight-test data for validation purposes, and results of a handling quality study during simulated ILS (instrument landing system) approaches and missed approaches are presented. Simulated flight trajectories, task performance measures, and pilot evaluations are presented for the ILS approach and missed-approach tasks conducted with the vehicle in the presence of moderate turbulence, varying horizontal winds and engine-out conditions. Six test subjects consisting of two research pilots, a Cessna test pilot, and three general aviation pilots participated in the study. This effort was undertaken in cooperation with the Cessna Aircraft Company.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4516 , L-17215 , NAS 1.15:4516
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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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
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