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  • 1
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    Supercooled Large Droplet Icing Flight Research Program (2000)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: During the past three winters, the NASA Glenn Research Center at Lewis Field conducted icing research flights throughout the Great Lakes region to measure the characteristics of a severe icing condition having Supercooled Large Droplets (SLD). SLD was implicated in the 1994 crash of the ATR-72 commuter aircraft. This accident focused attention on the safety hazard associated with SLD, and it led the Federal Aviation Administration (FAA) to identify the need for a better understanding of the atmospheric characteristics of this icing condition. In response to this need, Glenn developed a cooperative icing flight research program with the FAA, the National Center for Atmospheric Research, and the Atmospheric Environment Service of Canada. The primary objectives were to (1) characterize the SLD icing condition in terms of important icing-related parameters (such as cloud droplet size, cloud water content, and temperature), (2) develop and refine SLD icing weather forecast products, and (3) document and measure the effects of SLD ice accretions on aircraft performance.
    Keywords: Air Transportation and Safety
    Type: Research and Technology 1999; NASA/TM-2000-209639
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Update on SLD Engineering Tools Development (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The airworthiness authorities (FAA, JAA, Transport Canada) will be releasing a draft rule in the 2006 timeframe concerning the operation of aircraft in a Supercooled Large Droplet (SLD) environment aloft. The draft rule will require aircraft manufacturers to demonstrate that their aircraft can operate safely in an SLD environment for a period of time to facilitate a safe exit from the condition. It is anticipated that aircraft manufacturers will require a capability to demonstrate compliance with this rule via experimental means (icing tunnels or tankers) and by analytical means (ice prediction codes). Since existing icing research facilities and analytical codes were not developed to account for SLD conditions, current engineering tools are not adequate to support compliance activities in SLD conditions. Therefore, existing capabilities need to be augmented to include SLD conditions. In response to this need, NASA and its partners conceived a strategy or Roadmap for developing experimental and analytical SLD simulation tools. Following review and refinement by the airworthiness authorities and other international research partners, this technical strategy has been crystallized into a project plan to guide the SLD Engineering Tool Development effort. This paper will provide a brief overview of the latest version of the project plan and technical rationale, and provide a status of selected SLD Engineering Tool Development research tasks which are currently underway.
    Keywords: Air Transportation and Safety
    Type: NASA/TM-2004-213072 , E-14548 , Rept-2003-01-2127 , FAA In-Flight Icing/Ground De-Icing International Conference; Jun 16, 2003 - Jun 20, 2003; Chicago, IL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Validation of NASA Thermal Ice Protection Computer Codes (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental program was generated by the Icing Technology Branch at NASA Glenn Research Center to validate two ice protection simulation codes: (1) LEWICE/Thermal for transient electrothermal de-icing and anti-icing simulations, and (2) ANTICE for steady state hot gas and electrothermal anti-icing simulations. An electrothermal ice protection system was designed and constructed integral to a 36 inch chord NACA0012 airfoil. The model was fully instrumented with thermo-couples, RTD'S, and heat flux gages. Tests were conducted at several icing environmental conditions during a two week period at the NASA Glenn Icing Research Tunnel. Experimental results of running-wet and evaporative cases were compared to the ANTICE computer code predictions and are presented in this paper.
    Keywords: Air Transportation and Safety
    Type: NASA/TM-2001-210907/PT3 , E-12786/PT3 , NAS 1.15:210907/PT3 , AIAA Paper 97-0051 , 35th Aerospace Sciences Meeting and Exhibit; Jan 06, 1997 - Jan 07, 1997; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Freezing Rain as an In-Flight Icing Hazard (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Exposure to supercooled large drops (SLD-subfreezing water droplets with diameters greater than approx. 50 microns) can pose a significant threat to the safety of some aircraft. Although SLD includes both freezing drizzle (FZDZ) and freezing rain (FZRA), much of the SLD research and development of operational SLD forecast tools has focused on FZDZ and ignored FZRA, regarding is as less of a hazard to aviation. This paper provides a counterpoint case study that demonstrates FZRA as a significant in-flight icing hazard. The case study is based on flight and meteorological data from a joint NASA/FAA/NCAR SLD icing research project collected on February 4, 1998. The NASA Twin Otter Icing Research Aircraft experienced a prolonged exposure to "classical" FZRA that formed extensive ice formations including ridges and nodules on the wing and tail, and resulted in a substantial performance penalty. Although the case study provides only a singular FZRA event with one aircraft type, it is clear that classical FZRA can pose a significant in-flight icing hazard, and should not be ignored when considering SLD issues.
    Keywords: Air Transportation and Safety
    Type: NASA/TM-2000-210058 , E-12260 , NAS 1.15:210058 , Aviation, Range and Aerospace Meteorology; Jan 10, 1999 - Jan 15, 1999; Dallas, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Overview of High Speed Close-Up Imaging in an Icing Environment (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The Icing Branch and Imaging Technology Center at NASA Glenn Research Center have recently been involved in several projects where high speed close-up imaging was used to investigate water droplet impact/splash, and also ice particle impact/bounce in an icing wind tunnel. The combination of close-up and high speed imaging capabilities were required because the particles being studied were relatively small (d 〈 1 mm in diameter), and the impact process occurred in a very short time period (t(sub impact) 〈〈 1 sec). High speed close-up imaging was utilized to study the dynamics of droplet impact and splash in simulated Supercooled Large Droplet (SLD) icing conditions. The objective of this test was to evaluate the capability of a ultra high speed camera system to acquire quantitative information about the impact process (e.g., droplet size, velocity). Imaging data were obtained in an icing wind tunnel for spray cloud MVD 〉 50 m. High speed close-up imaging was also utilized to characterize the impact of ice particles on an airfoil with a thermally protected leading edge. The objective of this investigation was to determine whether ice particles tend to "stick" or "bounce" after impact. Imaging data were obtained for cases where the airfoil surface was heated and unheated. Based on the results from this test, follow on tests were conducted to investigate ice particle impact on the sensing elements of water content measurement devices. This paper will describe the use of the imaging systems to support these experimental investigations, present some representative results, and summarize what was learned about the use of these systems in an icing environment.
    Keywords: Air Transportation and Safety
    Type: NASA/TM-2004-212925 , AIAA Paper 2004-0407 , E-14357
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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