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  • Other Sources  (183)
  • AIRCRAFT  (125)
  • GENERAL  (58)
  • Analytical Chemistry and Spectroscopy
  • Cell & Developmental Biology
  • Chemical Engineering
  • 1970-1974  (183)
  • 1955-1959
  • 1974  (94)
  • 1973  (89)
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Source
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  • 1970-1974  (183)
  • 1955-1959
Year
  • 1
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    Suspension-line wave motion during the lines-first parachute unfurling process (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A new mathematical approach to modeling the lines-first parachute unfurling process is presented. The unfurling process is treated as two distinct phases: a suspension-line unfurling phase, during which a massless-spring model of the suspension-line elasticity may be employed; and a canopy unfurling phase, during which a formulation considering suspension-line wave mechanics is employed. Histories of unfurled length and tension at the vehicle obtained using the model are compared with flight test data, and generally good agreement is observed.
    Keywords: AIRCRAFT
    Type: AIAA Journal; 12; Jan. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The Influence of Wing Loading on Turbofan Powered STOL Transports with and Without Externally Blown Flaps (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of wing loading on the design of short takeoff and landing (STOL) transports using (1) mechanical flap systems, and (2) externally blown flap systems are determined. Aircraft incorporating each high-lift method are sized for field lengths of 2,000 feet, 2,500 feet, and 3,500 feet, and for payloads of 40, 150, and 300 passengers, for a total of 18 point-design aircraft. An assumed 1975 level of technology is applied to both concepts in terms of propulsion, weights, active controls, supercritical wing methodology, and acoustics. Low-wing-loading STOL configurations with mechanical flaps are found to be competitive with externally blown flap STOL configurations over wide ranges of payload and field length for the airworthiness rules and technology improvements assumed. Because the results of design studies like this one are sensitive to the ground rules assumed, careful attention is paid to describing the assumptions. These assumptions must be understood before the results are compared with other STOL airplane studies.
    Keywords: AIRCRAFT
    Type: NASA-CR-2320 , D3-8514-7
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    An analysis of pilot error-related aircraft accidents (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A multidisciplinary team approach to pilot error-related U.S. air carrier jet aircraft accident investigation records successfully reclaimed hidden human error information not shown in statistical studies. New analytic techniques were developed and applied to the data to discover and identify multiple elements of commonality and shared characteristics within this group of accidents. Three techniques of analysis were used: Critical element analysis, which demonstrated the importance of a subjective qualitative approach to raw accident data and surfaced information heretofore unavailable. Cluster analysis, which was an exploratory research tool that will lead to increased understanding and improved organization of facts, the discovery of new meaning in large data sets, and the generation of explanatory hypotheses. Pattern recognition, by which accidents can be categorized by pattern conformity after critical element identification by cluster analysis.
    Keywords: AIRCRAFT
    Type: NASA-CR-2444 , H-827
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Measurement of plasma temperature and density using radiation absorption (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A procedure, using a light beam of predetermined wavelength, preferably monochromatic, for measuring plasma characteristics is presented. Light absorbed by the plasma is used to obtain an absorption coefficient for the plasma. From this known coefficient and independent measurement of either the electron density or temperature of the plasma, an equation may be solved to obtain other unknown quantities. In this procedure, the absorption coefficient of the plasma is derived simultaneously for two probing light beams of substantially different predetermined wavelengths. These two coefficients are used to solve the two equations, which are in turn used to determine plasma electron density and temperature.
    Keywords: GENERAL
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Effect of exhaust nozzle configuration on aerodynamic and acoustic performance of an externally blown flap system with a quiet 6:1 bypass ratio engine (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A highly suppressed TF-34 engine was used to investigate engine and flap interaction noise associated with an externally blown flap STOL powered lift system. Noise, efficiency, and velocity decay characteristics of mixed and separate flow exhaust systems including convergent, co-annular, and lobed designs were determined with the engine operating alone. Noise data were then obtained for several of the exhaust configurations with the engine blowing a wing-flap segment. Noise for both the engine alone and the engine with blown flaps showed substantial differences for the various exhaust configurations tested. The differences in observed noise are related primarily to nozzle effective exhaust velocity, flap impingement velocity, and noise spectral shape.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-71466 , E-7765 , Propulsion Joint Specialist Conf.; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Applications of advanced aerodynamic technology to light aircraft. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses a project for adapting advanced technology, much of it borrowed from the jet transport, to general aviation design practice. The NASA funded portion of the work began in 1969 at the University of Kansas and resulted in a smaller, experimental wing with spoilers and powerful flap systems for a Cessna Cardinal airplane. Some flight data and research pilot comments are presented. The project was expanded in 1972 to include a light twin-engine airplane. For the twin there was the added incentive of a potential increase in single-engine climb performance. The use of a new high-lift Whitcomb airfoil is planned for both the wing and the propellers. Preliminary data on the characteristics of the new airfoil are discussed. The configuration of an experimental wing for a Piper Seneca PA-34 and estimated airplane performance with this wing are discussed.
    Keywords: AIRCRAFT
    Type: SAE PAPER 730318 , Business Aircraft Meeting; Apr 03, 1973 - Apr 06, 1973; Wichita, KS
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Wind tunnel investigation of effects of variations in Reynolds number and leading-edge treatment on the aerodynamic characteristics of an externally blown jet-flap configuration (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted in a full-scale tunnel to determine the effects of variations in Reynolds number and leading-edge treatment on the aerodynamic characteristics of an externally blown jet-flap transport configuration. The model had a double-slotted trailing-edge flap and was powered by four high-bypass-ratio turbofan engines. Tests were performed by using each of three leading-edge devices (a 30-percent-chord flap and 15- and 25-percent-chord slats) at Reynolds numbers from 0.47 x one million to 1.36 x one million thrust coefficients up to 3.5. The use of a 25-percent-chord slat was found to be more effective than a 15-percent-chord slat or a 30-percent-chord flap in extending the stall angle of attack and in minimizing the loss of lift after the stall. The large slat was also effective in reducing the rolling moments that occurred when the engine-out wing stalled first.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7194 , L-8745
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Simulation of decelerating landing approaches on an externally blown flap STOL transport airplane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fixed-base simulator program was conducted to define the problems and methods for solution associated with performing decelerating landing approaches on a representative STOL transport having a high wing and equipped with an external-flow jet flap in combination with four high-bypass-ratio fan-jet engines. Real-time digital simulation techniques were used. The computer was programed with equations of motion for six degrees of freedom and the aerodynamic inputs were based on measured wind-tunnel data. The pilot's task was to capture the localizer and the glide slope and to maintain them as closely as possible while decelerating from an initial airspeed of 140 knots to a final airspeed of 75 knots, while under IFR conditions.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7463 , L-9242
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Transmitting and reflecting diffuser (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A near-Lambertian diffuser is described which transmits and reflects ultraviolet light. An ultraviolet grade fused silica substrate is coated with vaporized fuse silica. The coating thickness is controlled, one thickness causing ultraviolet light to diffuse and another thickness causing ultraviolet light to reflect a near Lambertian pattern.
    Keywords: GENERAL
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Wind tunnel tests of an F-8 airplane model equipped with an oblique wing (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted in an 11- by 11-foot transonic wind tunnel to study the lift, drag and stability characteristics of a 0.087-scale model of an operational airplane fitted with an oblique wing. The model wing was of elliptical planform with an unswept aspect ratio of 12.7 and a thickness of 10 percent. All other external geometric features of the model were scaled to the basic full size operational airplane with the engine inlet faired closed. Longitudinal and lateral-directional stability data were obtained with the wing at sweep angles of 0 deg, 45 deg and 60 deg Test Mach numbers ranged from 0.6 to 1.4 deg Angles of attack were between minus 4 deg and 8 deg at zero sideslip. Angles of sideslip were between plus and minus 4 degrees for two angles of attack depending upon the wing configuration. Tests were conducted at a Reynolds number of 6 million per foot except for a few runs when balance capacity limited the Reynolds number to 4 million per foot.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62273
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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