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  • 1
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    Spinning for safety's sake (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: NASA Langley is currently engaged in a comprehensive research program to improve the stall/spin characteristics of general aviation airplanes. Part of this program has included systematic flight tests of a fully instrumented airplane to determine the effects of various tail, wing, and fuselage modifications, and variation of inertia, center-of-gravity, and control positions on the spin and recovery characteristics. Airplane equipment, onboard instrumentation ground equipment, test area, and test procedures have been combined to provide a safe, practical means for conducting research in preplanned hazardous conditions. Configuration changes produced spins varying from easily recoverable to unrecoverable, and wind section design significantly influenced airplane stall, spin, and recovery characteristics.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: SAFE Journal; 10; Fall 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Discontinuous wing leading edge to enhance spin resistance (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 283-288
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Applications of dynamic stability parameters to problems in aircraft dynamics (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The application and analysis of dynamic stability parameters were examined. The effects of wing leading edge modifications on the stalling and spinning characteristics of a single engine general aviation research airplane are evaluated. It is illustrated how dynamic stability parameters measured in wind tunnel tests are used to predict the spin resistance of this class of aircraft, and that autorotation criteria are derived from the relationships which exist between static and dynamic aerodynamic characteristics.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AGARD Dyn. Stability Parameters; 12 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    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
  • 5
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    Leading-edge design for improved spin resistance of wings incorporating conventional and advanced airfoils (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Discontinuous wing leading-edge droop designs have been evaluated as a means of modifying wing autorotative characteristics and thus improving airplane spin resistance. Addition of a discontinuous outboard wing leading-edge droop to three typical light airplanes having NACA 6-series wing sections produced significant improvements in stall characteristics and spin resistance. Wind tunnel tests of two wings having advanced natural laminar flow airfoil sections indicated that a discontinuous leading-edge droop can delay the onset of autorotation at high angles of attack without adversely affecting the development of laminar flow at cruise angles of attack.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 851816
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Flight investigation of an on-off control for V/STOL aircraft under visual conditions (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Helicopter flight test of on-off pitch and roll control for V/STOL aircraft under visual conditions
    Keywords: AIRCRAFT
    Type: NASA-TN-D-3436
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Wing modification for increased spin resistance (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A simple wing leading-edge modification has been developed that delays outer wing panel stall, thus maintaining roll damping to higher angles of attack and delaying the onset of autorotation. The stall angle of attack of the outer wing panel has been shown to be a function of the spanwise length of the leading-edge modification. The margin of spin resistance provided by the modification is being explored through flight tests. Preliminary results have been used to evaluate spin resistance in terms of the difference in angle of attack between outer wing panel stall and the maximum attainable angle of attack.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: SAE PAPER 830720
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Use of a discontinuous wing leading-edge modification to enhance spin resistance for general aviation airplanes (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Spin resistance of two typical general aviation airplanes has been studied. Improvement in spin resistance due to an outboard wing leading-edge modification was evaluated through wind-tunnel and flight tests. The basic airplanes would readily enter a spin; however, with the wing modification the airplanes were highly spin resistant. Spin resistance has been related to the angle of attack of the outer wing panel and the yaw rate as a step toward development of guidelines for design of more spin resistant airplanes.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 84-0559
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Flight investigation of stall, spin and recovery characteristics of a low-wing, single-engine, T-tail light airplane (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight tests were performed to investigate the stall, spin, and recovery characteristics of a four-place, low-wing, single-engine, T-tail, general aviation research airplane at an aft center-of-gravity position. Most stalls resulted in roll-offs. Spins were oscillatory in roll and pitch at 43 deg angle of attack; the magnitude of the oscillations was determined by aileron position. Power, flap deflection, and landing gear position did not affect the angle of attack to the spin. Antispin rudder followed by forward wheel with ailerons neutral produced the fastest and most consistent recoveries but the initial application of recovery controls did not always stop a spin.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-2427 , L-15868 , NAS 1.60:2427
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Operational experiences of a commercial helicopter flown in a large metropolitan area (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A survey of commercial helicopter-operating experiences was conducted using a helicopter flight recorder in order to provide a basis for extending helicopter design and service-life criteria. These data are representative of 182 flight hours accumulated during 1414 flights comprised of the separate legs of the total route structure employed. The operating experiences are presented in terms of the time spent within different airspeed brackets, within the classifiable flight conditions of climb, en route, and descent, at various rates of climb and descent, and at different rotor rotational speeds. The results indicated that the helicopter spent a majority of the flight time at airspeeds either below 40 knots or above 100 knots. Rates of climb and descent were concentrated at values below 5.1 m/s (1000 ft/min) particularly for higher airspeeds. Normal acceleration experiences were low, both in the total number and peak value realized; however, an extremely large number of pitch angular-velocity experiences were noted. Rotor rotational speeds were normal with no occurrences above the upper red-line limit.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-TN-D-8000 , L-10149
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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