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  • 1
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    NASA's aircraft icing analysis program (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An overview of the NASA ongoing efforts to develop an aircraft icing analysis capability is presented. Discussions are included of the overall and long term objectives of the program as well as current capabilities and limitations of the various computer codes being developed. Descriptions are given of codes being developed to analyze two- and three-dimensional trajectories of water droplets, airfoil ice accretion, aerodynamic performance degradation of components and complete aircraft configurations, electrothermal deicer, fluid freezing point depressant antideicer and electro-impulse deicer. The need for bench mark and verification data to support the code development is also discussed, and selected results of experimental programs are presented.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The performance characteristics of simulated ice on rotorcraft airfoils (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Attention is given to the results of NASA-sponsored rotorcraft icing research which was aimed at the formulation of a predictive method for the computation of performance penalties due to rotor and airfoil icing. Parametric simulated ice test results obtained in wind tunnels are compared with those of other investigations. These comparisons indicate that proper design of simulated ice shapes can adequately represent ice on airfoil sections, with incremental lift, drag, and pitching moments matching those generated in icing wind tunnels.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    NASA's program on icing research and technology (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: NASA's program in aircraft icing research and technology is reviewed. The program relies heavily on computer codes and modern applied physics technology in seeking icing solutions on a finer scale than those offered in earlier programs. Three major goals of this program are to offer new approaches to ice protection, to improve the ability to model the response of an aircraft to an icing encounter, and to provide improved techniques and facilities for ground and flight testing. The following program elements are reviewed: (1) new approaches to ice protection; (2) numerical codes for deicer analysis; (3) measurement and prediction of ice accretion and its effect on aircraft and aircraft components; (4) special wind tunnel test techniques for rotorcraft icing; (5) improvements of icing wind tunnels and research aircraft; (6) ground de-icing fluids used in winter operation; (7) fundamental studies in icing; and (8) droplet sizing instruments for icing clouds.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AGARD, Flight in Adverse Environmental Conditions; 31 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    NASA's rotorcraft icing research program (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The objective of the NASA aircraft icing research program is to develop and make available icing technology to support the needs and requirements of industry for all weather aircraft designs. While a majority of the technology being developed is viewed to be generic (i.e., appropriate to all vehicle classes), vehicle specific emphasis is being placed on the helicopter due to its unique icing problems. In particular, some of the considerations for rotorcraft icing are indicated. The NASA icing research program emphasizes technology development in two key areas: ice protection concepts and icing simulation (analytical and experimental). The NASA research efforts related to rotorcraft icing in these two technology areas will be reviewed.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA, Washington, NASA(Army Rotorcraft Technology. Volume 2: Materials and Structures, Propulsion and Drive Systems, Flight Dynamics and Control, and Acoustics; p 802-832
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The NASA aircraft icing research program (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The objective of the NASA aircraft icing research program is to develop and make available to industry icing technology to support the needs and requirements for all weather aircraft designs. Research is being done for both fixed and rotary wing applications. The NASA program emphasizes technology development in two key areas: advanced ice protection concepts and icing simulation (analytical and experimental). The computer code development/validation, icing wind tunnel testing, and icing flight testing efforts which were conducted to support the icing technology development are reviewed.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: Aeropropulsion '87. Session 5: Subsonic Propulsion Technology; 27 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Performance degradation of helicopter rotor in forward flight due to ice (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This study addresses the analytical assessment of the degradation in the forward flight performance of the front rotor Boeing Vertol CH47D helicopter in a rime ice natural icing encounter. The front rotor disk was divided into 24 15-deg sections and the local Mach number and angle of attack were evaluated as a function of azimuthal and radial location for a specified flight condition. Profile drag increments were then calculated as a function of azimuthal and radial position for different times of exposure to icing, and the rotor performance was re-evaluated including these drag increments. The results of the analytical prediction method, such as horsepower required to maintain a specific flight condition, as a function of icing time have been generated. The method to illustrate the value of such an approach in assessing performance changes experienced by a helicopter rotor as a result of rime ice accretion is described.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 713-718
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Particle trajectory computer program for icing analysis of axisymmetric bodies - A progress report (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Aircraft exposed to an atmospheric icing environment can accumulate ice, resulting in a sharp increase in drag, a reduction in lift, control surface fouling, and engine damage all of which result in a hazardous flight situation. NASA Lewis Research Center (LeRC) has conducted a program to examine, with the aid of high-speed computer codes, how the trajectories of particles contribute to the ice accumulation on airfoils and engine inlets. For this effort, a computer code was developed to calculate icing particle trajectories and impingement limits for axisymmetric inlets. The original research-oriented NASA code was upgraded and modified to meet the requirements of the design engineer. The improved code is capable of performing trajectory calculations for any atmospheric conditions and droplet sizes. It can handle single droplets or a distribution of various droplet sizes. The four programs that comprise the code are described and the results of a test case using flight conditions for a Fokker F100 icing tunnel test are presented.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 87-0027
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    The UH-1H helicopter icing flight test program - An overview (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An ongoing joint NASA/Army program to study the effects of ice accretion on unprotected helicopter rotor aerodynamic performance is discussed. This program integrates flight testing, wind tunnel testing, and analytical modeling. Results are discussed for helicopter flight testing in the Canadian NRC hover spray rig facility to measure rotor aero performance degradation and document rotor ice accretion characteristics. The results of dry wind tunnel testing of airfoil sections with artificial ice accretions and predictions of rotor performance degradation using available rotor performance codes and the wind tunnel data are presented. An alternative approach to conducting future helicopter icing flight programs is discussed.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 85-0338
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    NASA's Aircraft Icing Analysis Program (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: An overview of the NASA ongoing efforts to develop an aircraft icing analysis capability is presented. Discussions are included of the overall and long term objectives of the program as well as current capabilities and limitations of the various computer codes being developed. Descriptions are given of codes being developed to analyze two and three dimensional trajectories of water droplets, airfoil ice accretion, aerodynamic performance degradation of components and complete aircraft configurations, electrothermal deicer, fluid freezing point depressant antideicer and electro-impulse deicer. The need for bench mark and verification data to support the code development is also discussed, and selected results of experimental programs are presented.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-TM-88791 , E-3121 , NAS 1.15:88791 , International Conference of the Aeronautical Sciences (ICAS); 7-12 Sept. 1986; London
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Evaluation of icing drag coefficient correlations applied to iced propeller performance prediction (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Evaluation of three empirical icing drag coefficient correlations is accomplished through application to a set of propeller icing data. The various correlations represent the best means currently available for relating drag rise to various flight and atmospheric conditions for both fixed-wing and rotating airfoils, and the work presented here ilustrates and evaluates one such application of the latter case. The origins of each of the correlations are discussed, and their apparent capabilities and limitations are summarized. These correlations have been made to be an integral part of a computer code, ICEPERF, which has been designed to calculate iced propeller performance. Comparison with experimental propeller icing data shows generally good agreement, with the quality of the predicted results seen to be directly related to the radial icing extent of each case. The code's capability to properly predict thrust coefficient, power coefficient, and propeller efficiency is shown to be strongly dependent on the choice of correlation selected, as well as upon proper specificatioon of radial icing extent.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: SAE PAPER 871033
    Format: text
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