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  • Other Sources  (38)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE
  • 2020-2023
  • 1980-1984  (38)
  • 1940-1944
  • 1983  (38)
  • 1
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    Operational military helicopter interior noise and vibration measurements with comparisons to ride quality criteria (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Balka (1981) has identified the attainment of a 'jet-smooth' ride as a primary goal of the helicopter industry for commercial and certain military helicopters. It was noted that criteria accounting for both multiple axis vibration and interior noise are needed. The present investigation has the objective to present a vibration and interior noise data base in a format suitable for direct evaluation of aircraft ride quality. The investigation is also concerned with an assessment of the measured environment against available criteria as an indication of the state-of-the-art for current machines. Interior noise and vibration measurements were obtained on eight military helicopters during routine operational flights. The data are presented in the form of a number of parameters.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-2526
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    AFTI/F-16 flight test results and lessons (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The AFTI/F-16 flight test program is summarized, and several design issues of general interest are addressed. A brief description is given of the test vehicle, its flight control modes, and the flight envelopes in which testing was performed. Flight test results are summarized by addressing benefits experienced in flight control task-tailoring, handling qualities in mission tasks, aircraft structure considerations, digital flight control system performance, and human factors. Finally, several design issues relevant to future fighter aircraft are examined, including degraded flight control, system complexity, simplex information in redundant systems, and single failure propagation in redundant systems.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Interior noise considerations for advanced high-speed turboprop aircraft (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 17, p. 2685, Accession no. A82-35018
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0021-8669)
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Status review of a supersonically-biased fighter wing-design study (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Results from an ongoing supersonically-biased fighter wing-design study are summarized. The study has been conducted to explore the effects of supersonic aerodynamic performance, transonic maneuvering, low-speed/high angle-of-attack characteristics, and airframe system integration requirements on fighter aircraft wing design. The approach adopted involves the theoretical and experimental investigation of four advanced aircraft configurations which differ only in wing geometry. Supersonic and low-speed/high angle-of-attack wind tunnel results have been obtained for 20 deg trapezoidal, 65 deg delta, 70/30-deg advanced cranked, and 70/66-deg advanced cranked wing configurations. The supersonic data show that the advanced cranked wings outperform the trapezoidal and delta wings at cruise and moderate lift conditions. Low-speed/high angle-of-attack results show that all wings have significant stability problems above an angle of attack of 20 deg. Aircraft sizing analysis results show that the advanced cranked-wing configurations are significantly lighter, based upon take-off gross weight, than either the trapezoidal or the delta wings.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1857
    Format: text
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  • 5
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    Application of in-flight thrust determination uncertainty (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A numerical example is given of a previously proposed methodology for the evaluation of in-flight thrust measurement uncertainty, using data extracted from a performance report comparing two different missile prototypes under a variety of flight conditions. Attention is given to the data for the AGM-68B Air Launched Cruise Missile, which is powered by the F107 dual-spool, mixed flow turbofan engine. Assessments are made of the definition of the measurement process, instrumentation error estimation, the propagation of errors to thrust calculation, mathematical model errors, the in-flight thrust error component, and correction to standard conditions. It is concluded that in-flight thrust measurement uncertainty limits can be evaluated from measurement system error analysis results and test data for the missile evaluation process presently described.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 831439
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Uncertainty methodology for in-flight thrust determination (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A methodology is proposed for the evaluation of uncertainty in the in-flight determination of aircraft thrust, which provides error traceability to a national standards laboratory, and is independent of the procedure used to calculate or measure thrust in flight, thereby yielding a consistent means for the evaluation of measurement capabilities. Attention is given to the factors of measurement error, precision, bias, uncertainty, error estimation and classification, error propagation, ground testing, and the related problems of model bias error, model precision error, and the uncertainty limit.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 831438
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Subsonic panel method for designing wing surfaces from pressure distribution (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An iterative method has been developed for designing wing section contours corresponding to a prescribed subcritical distribution of pressure. The calculations are initialized by using a surface panel method to analyze a baseline wing or wing-fuselage configuration. A first-order expansion to the baseline panel method equations is then used to calculate a matrix containing the partial derivative of potential at each control point with respect to each unknown geometry parameter. In every iteration cycle, the matrix is used both to calculate the geometry perturbation and to analyze the perturbed geometry. The distribution of potential on the perturbed geometry is established by simple linear extrapolation from the baseline solution. The extrapolated potential is converted to pressure by Bernoulli's equation. Not only is the accuracy of the approach good for very large perturbations, but the computing cost of each complete iteration cycle is substantially less than one analysis solution by a conventional panel method.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-3713 , NAS 1.26:3713
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A study of altitude and flight path angle dynamics for a singularly perturbed fuel optimization problem (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: This short paper will demonstrate that the separation of altitude and flight path angle dynamics using singular perturbation techniques for a transport fuel optimization problem results in an unacceptable oscillation in altitude. A technique for damping this oscillation by adding a penalty term to the cost function for the optimization problem will be discussed. This technique will be compared with a different approach that linearizes the altitude and flight path angle boundary layers.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Experience with flight test trajectory guidance (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 3, p. 325, Accession no. A82-14379
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0731-5090)
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Instrumentation and data processing for AFTI/F-16 flight testing (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The primary objective of the advanced fighter technology integration/F-16 (AFTI/F-16) development program is to demonstrate advanced fighter technologies to improve weapon delivery and aircraft survivability. Instrumentation and data processing for monitoring aircraft operation during flight testing is necessary not only for safety-of-flight considerations but also for rapid evaluation of flight test results. The complexity of the AFTI/F-16 aircraft necessitates an extensive capability to accomplish data goals; this paper describes that capability and the resultant product.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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