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  • 1
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    Unknown
    Development of spin resistance criteria for light general aviation airplanes (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A brief history of stall/spin technology for light general aviation airplanes is presented. Criteria needed to describe desirable characteristics of a spin-resistant airplane and means to evaluate airplanes for compliance with the criteria have been developed. Initial results from limited flight tests of an experimental high-wing airplane indicated that the basic configuration would not meet the spin resistance criteria. Further tests with the airplane modified to enhance its spin resistance are planned.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 86-9812
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A simulation study of the low-speed characteristics of a light twin with an engine-out (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Potential safety advantages provided by the two engines on a light twin aircraft are not realized in practice as evidenced by recent engine-failure accident statistics. These statistics showed twice the fatality rate from engine failure for twins as for single-engine aircraft. The statistics showed also that one-half of the fatal engine-out accidents involved a stall. An improvement of the low-speed engine-out characteristics is, therefore, needed. An investigation of the engine-out characteristics of light twin-engine aircraft is currently being conducted as part of the comprehensive stall/spin program for general aviation aircraft. The present study is concerned with the first phase of this program. The primary objective of this study is to advance the understanding of the basic flight dynamics and piloting problems for an engine-out condition. An all-digital computer system was used in the conducted simulation study.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 83-2128
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Exploratory piloted simulator study of the effects of winglets on handling qualities of a representative agricultural airplane (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects on handling qualities of adding winglets to a representative agricultural aircraft configuration during swath-run maneuvering were evaluated. Aerodynamic data used in the simulation were based on low-speed wind tunnel tests of a full scale airplane and a subscale model. The Cooper-Harper handling qualities rating scale, supplementary pilot comments, and pilot vehicle performance data were used to describe the handling qualities of the airplane with the different wing-tip configurations. Results showed that the lateral-directional handling qualities of the airplane were greatly affected by the application of winglets and winglet cant angle. The airplane with winglets canted out 20 deg exhibited severely degraded lateral directional handling qualities in comparison to the basic airplane. When the winglets were canted inward 10 deg, the flying qualities of the configuration were markedly improved over those of the winglet-canted-out configuration or the basic configuration without winglets, indicating that proper tailoring of the winglet design may afford a potential benefit in the area of handling qualities.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-81817
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Simulator study of stall/post-stall characteristics of a fighter airplane with relaxed longitudinal static stability (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A real-time piloted simulation was conducted to evaluate the high-angle-of-attack characteristics of a fighter configuration based on wind-tunnel testing of the F-16, with particular emphasis on the effects of various levels of relaxed longitudinal static stability. The aerodynamic data used in the simulation was conducted on the Langley differential maneuvering simulator, and the evaluation involved representative low-speed combat maneuvering. Results of the investigation show that the airplane with the basic control system was resistant to the classical yaw departure; however, it was susceptible to pitch departures induced by inertia coupling during rapid, large-amplitude rolls at low airspeed. The airplane also exhibited a deep-stall trim which could be flown into and from which it was difficult to recover. Control-system modifications were developed which greatly decreased the airplane susceptibility to the inertia-coupling departure and which provided a reliable means for recovering from the deep stall.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1538 , L-12854
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Simulation study of an automatic trim system for reducing the control forces on a light twin after an engine failure (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An automatic trim system for reducing the control forces after an engine failure on a light twin has been investigated on the Langley General Aviation Simulator. The system schedules open-loop trim tab deflections as a function of differential propeller slipstream dynamic pressure and freestream dynamic pressure. The system is described and the airplane-system static and dynamic characteristics are documented. Three NASA research pilots evaluated the effectiveness of the system for takeoff and landing maneuvers. A variety of off-nominal system characteristics were studied. The system was judged to be generally beneficial, providing a 2 to 3 point improvement in pilot rating for the tasks used in the evaluations.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: SAE PAPER 850913
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Investigations of modifications to improve the spin resistance of a high-wing, single-engine, light airplane (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A general aviation aircraft with drooped leading edge modifications for improvement of lateral stability at high angles of attack has been flight tested in combination with a ventral fin which improves directional stability. The two modifications were assessed in light of spin-resistance criteria proposed for incorporation into FAA certification regulations. The configuration combining outboard wing leading-edge droop and a ventral fin yielded a substantial increase in spin resistance, but fell short of all requirements encompassed by the proposed spin-resistance criteria.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: SAE PAPER 891039
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Simulator results of an F-14A airplane utilizing an aileron-rudder interconnect during carrier approaches and landings (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A piloted simulator study was conducted to evaluate an aileron rudder interconnect (ARI) control system for the F-14A airplane in the landing configuration. Effects on pilot performance and handling characteristics were investigated. Two ARI configurations were tested and compared to the standard F-14 fleet control system. A nonlinear aerodynamic model of the F-14 was used in conjunction with a six degree of freedom motion base simulator. The evaluation task, which utilized three subject pilots, consistent of a night carrier approach and landing. Both ARI configurations produced improved pilot performance and pilot ratings when compared to the standard control system. Sideslip due to adverse yaw as considerably reduced by the ARI systems and heading control was more stable and precise. Lateral deviation from centerline was reduced during the approach and lateral touchdown dispersion on the carrier deck was reduced with the ARI control systems.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-81833
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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