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  • 1
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    Multistroke cloud-to-ground strike to the NASA F-106B airplane (1990)
    American Geophysical Union
    Details
    Publication Date: 1990-01-01
    Print ISSN: 0148-0227
    Electronic ISSN: 2156-2202
    Topics: Geosciences
    Published by American Geophysical Union
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    PAPER CURRENT
  • 2
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    Multistroke cloud-to-ground strike to the NASA F-106B airplane (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An analysis of electromagnetic waveform records and video images of a multistroke cloud-to-ground (CG) strike to the NASA F-106B instrumented airplane is presented. The CG flash started as a lightning strike triggered by the airplane and later produced multiple return strokes to the ground (the ground strike network registered six return strokes). Although there are some uncertainties in data interpretation resulting from lack of independent measurements with other than the airborne instruments, recoil streamers and eight sequences of dart leaders followed by return strokes (two more than were indicated by the ground network) were identified in the airborne data. At least three of the subsequent return strokes were attached to the airplane. The analysis provides evidence that formation of recoil streamers and dart leaders is accompanied by a surge in continuous current. This feature is similar to that observed in the bidirectional leader development during lightning initiation on the airplane.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: Journal of Geophysical Research (ISSN 0148-0227); 95; 5471-548
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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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
  • 4
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    The vortex flap F-106B, overcoming safety and data problems in flight testing (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A NASA, F-106B airplane equipped with a vortex flap is establishing a data base for calibration of design and analysis tools for this vortical flow control concept. Some of the problems in safely and precisely flying to research data points were caused by the modified airplane's low longitudinal stability and low margin of structural strength. These characteristics are, in part, a consequence of the program's low cost approach which utilizes a bolt-on, ground-adjustable flap attached to a minimally modified airplane. Presently, the 40-degree flap deflection flight research is being concluded with a flow visualization phase. A similar pattern of flight envelope expansion, pressure distribution, performance, and flow visualization phases remain to be accomplished for the 30-degree flap setting. To date, good research flight data has followed resolution of the safety and data problems described.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 90-1280
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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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
  • 6
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    High-Alpha Research Vehicle (HARV) longitudinal controller: Design, analyses, and simulation resultss (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the design, analysis, and nonlinear simulation results (batch and piloted) for a longitudinal controller which is scheduled to be flight-tested on the High-Alpha Research Vehicle (HARV). The HARV is an F-18 airplane modified for and equipped with multi-axis thrust vectoring. The paper includes a description of the facilities, a detailed review of the feedback controller design, linear analysis results of the feedback controller, a description of the feed-forward controller design, nonlinear batch simulation results, and piloted simulation results. Batch simulation results include maximum pitch stick agility responses, angle of attack alpha captures, and alpha regulation for full lateral stick rolls at several alpha's. Piloted simulation results include task descriptions for several types of maneuvers, task guidelines, the corresponding Cooper-Harper ratings from three test pilots, and some pilot comments. The ratings show that desirable criteria are achieved for almost all of the piloted simulation tasks.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-3446 , L-17323 , NAS 1.60:3446
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Cloud-to-ground strikes to the NASA F-106 airplane (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Cloud-to-ground (CG) lightning strike data on the NASA F-106B research aircraft obtained during the 1984-86 storm seasons in the vicinity of Wallops Island, Virginia, are analyzed. The results suggest that CG strikes may represent a significant portion of the total number of lightning strikes encountered by the aircraft at altitudes below 6 km. It is unlikely that an aircraft encounters the first return stroke of the CG flash. The current values of the CG strikes are not different from currents in other types of strikes.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 88-0390
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Cockpit display of ground-based weather data during thunderstorm research flights (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes an integrated system for providing ground-based cockpit display, transmitting to an aircraft, upon request via VHF radio, important ground-based thunderstorm data such as radar precipitation reflectivity contours, aircraft ground track, and cloud-to-ground lightning locations. Examples of the airborne X-band weather radar display and the ground-based display are presented for two different missions during the NASA Storm Hazards Program. In spite of some limitation, the system was found to be helpful in the selection of the route of flight, the general ground track to be used, and, occasionally, in clarifying the location of a specific cell of interest.
    Keywords: AERONAUTICS (GENERAL)
    Type: AIAA PAPER 89-0806
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Flight test results for several light, canard-configured airplanes (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Brief flight evaluations of two different, light, composite constructed, canard and winglet configured airplanes were performed to assess their handling qualities; one airplane was a single engine, pusher design and the other a twin engine, push-pull configuration. An emphasis was placed on the slow speed/high angle of attack region for both airplanes and on the engine-out regime for the twin. Mission suitability assessment included cockpit and control layout, ground and airborne handling qualities, and turbulence response. Very limited performance data was taken. Stall/spin tests and the effects of laminar flow loss on performance and handling qualities were assessed on an extended range, single engine pusher design.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 871801
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Final results of the NASA storm hazards program (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Keywords: METEOROLOGY AND CLIMATOLOGY
    Type: NOAA, International Aerospace and Ground Conference on Lightning and Static Electricity. Addendum; p 113-130
    Format: text
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    NASA TECHNICAL REPORTS
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