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  • 11
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    Hazard alerting and situational awareness in advanced air transport cockpits (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Advances in avionics and display technology have significantly changed the cockpit environment in current 'glass cockpit' aircraft. Recent developments in display technology, on-board processing, data storage, and datalinked communications are likely to further alter the environment in second and third generation 'glass cockpit' aircraft. The interaction of advanced cockpit technology with human cognitive performance has been a major area of activity within the MIT Aeronautical Systems Laboratory. This paper presents an overview of the MIT Advanced Cockpit Simulation Facility. Several recent research projects are briefly reviewed and the most important results are summarized.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Langley Research Center, Joint University Program for Air Transportation Research, 1991-1992; p 35-45
    Format: application/pdf
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  • 12
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    Alert generation and cockpit presentation for an integrated microburst alerting system (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Alert generation and cockpit presentation issues for low level wind shear (microburst) alerts are investigated. Alert generation issues center on the development of a hazard criterion which allows integration of both ground based and airborne wind shear detection systems to form an accurate picture of the aviation hazard posed by a particular wind shear situation. A methodology for the testing of a hazard criteria through flight simulation has been developed, and has been used to examine the effectiveness and feasibility of several possible criteria. Also, an experiment to evaluate candidate graphical cockpit displays for microburst alerts using a piloted simulator has been designed.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Langley Research Center, Joint University Program for Air Transportation Research, 1990-1991; p 29-39
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  • 13
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    Deterministic multi-zone ice accretion modeling (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The focus here is on a deterministic model of the surface roughness transition behavior of glaze ice. The initial smooth/rough transition location, bead formation, and the propagation of the transition location are analyzed. Based on the hypothesis that the smooth/rough transition location coincides with the laminar/turbulent boundary layer transition location, a multizone model is implemented in the LEWICE code. In order to verify the effectiveness of the model, ice accretion predictions for simple cylinders calculated by the multizone LEWICE are compared to experimental ice shapes. The glaze ice shapes are found to be sensitive to the laminar surface roughness and bead thickness parameters controlling the transition location, while the ice shapes are found to be insensitive to the turbulent surface roughness.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Langley Research Center, Joint University Program for Air Transportation Research, 1990-1991; p 19-28
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  • 14
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    Experimental investigation of passive infrared ice detection for helicopter applications (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A technique is proposed to remotely detect rotor icing on helicopters. Using passive infrared (IR) thermometry, it is possible to detect the warming caused by latent heat released as supercooled water freezes. During icing, the ice accretion region on the blade leading edge will be warmer than the uniced trailing edge, resulting in a chordwise temperature profile characteristic of icing. Preliminary tests were conducted on a static model in the NASA Icing Research Tunnel for a variety of wet (glaze) and dry (rime) ice conditions. The characteristic chordwise temperature profiles were observed with an IR thermal video system and confirmed with thermocouple measurements. A prototype detector system was built consisting of a single point IR pyrometer. Experiments were run on a small scale rotor model. Again, the characteristic chordwise temperature profiles were observed during icing, and the IR system was able to remotely detect icing. Based on the static and subscale rotor tests, the passive IR technique is promising for rotor ice detection.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Langley Research Center, Joint University Program for Air Transportation Research, 1990-1991; p 11-18
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  • 15
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    In-flight measurement of ice growth on an airfoil using an array of ultrasonic transducers (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of preliminary tests to measure ice growth on an airfoil during flight icing conditions are presented. Ultrasonic pulse echo measurements of ice thickness are obtained from an array of eight ultrasonic transducers mounted flush with the leading edge of the airfoil. These thickness measurements are used to document the evolution of the ice shape during the encounter in the form of successive ice profiles. Results from 3 research flights are presented and discussed. The accuracy of the ultrasonic measurements is found to be within 0.5 mm of mechanical and stereo photograph measurements of the ice accretion.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA-87-0178 , AIAA PAPER 87-0178 , NASA, Langley Research Center, Joint University Program for Air Transportation Research, 1986; p 7-15
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  • 16
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    Investigation of surface water behavior during glaze ice accretion (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Microvideo observations of glaze ice accretions on 1-in-diameter cylinders in a closed-loop refrigerated wind tunnel were obtained to study factors controlling the behavior of unfrozen surface water during glaze ice accretion. Three zones of surface water behavior were noted, each with a characteristic roughness. The effect of substrate thermal and roughness properties on ice accretions was also studied. The contact angle and hysteresis were found to increase sharply at temperatures just below 0 C, explaining the high resistance to motion of water beads observed on accreting glaze ice surfaces. Based on the results, a simple multizone modification to the current glaze ice accretion model is proposed.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 88-0115
    Format: text
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  • 17
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    An experimental and theoretical study of the ice accretion process during artificial and natural icing conditions (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Real-time measurements of ice growth during artificial and natural icing conditions were conducted using an ultrasonic pulse-echo technique. This technique allows ice thickness to be measured with an accuracy of + or - 0.5 mm; in addition, the ultrasonic signal characteristics may be used to detect the presence of liquid on the ice surface and hence discern wet and dry ice growth behavior. Ice growth was measured on the stagnation line of a cylinder exposed to artificial icing conditions in the NASA Lewis Icing Research Tunnel (IRT), and similarly for a cylinder exposed in flight to natural icing conditions. Ice thickness was observed to increase approximately linearly with exposure time during the initial icing period. The ice accretion rate was found to vary with cloud temperature during wet ice growth, and liquid runback from the stagnation region was inferred. A steady-state energy balance model for the icing surface was used to compare heat transfer characteristics for IRT and natural icing conditions. Ultrasonic measurements of wet and dry ice growth observed in the IRT and in flight were compared with icing regimes predicted by a series of heat transfer coefficients. The heat transfer magnitude was generally inferred to be higher for the IRT than for the natural icing conditions encountered in flight. An apparent variation in the heat transfer magnitude was also observed for flights conducted through different natural icing-cloud formations.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-CR-182119 , NAS 1.26:182119 , DOT/FAA/CT-87/17
    Format: application/pdf
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  • 18
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    In-flight measurement of ice growth on an airfoil using an array of ultrasonic transducers (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Results from three research flights to obtain in-flight ultrasonic pulse-echo measurements of airfoil ice thickness as a function of time using an array of eight ultrasonic transducers mounted flush with the leading edge of the airfoil are presented. The accuracy of the thickness measurements is found to be within 0.5 mm of mechanical and stereophotograph measurements of the ice accretion. The ultrasonic measurements demonstrate that the ice growth rate typically varies during the flight, with variations in the ice growth rate for dry ice growth being primarily due to fluctuations in the cloud liquid water content. Discrepancies between experimental results and results predicted by an analytic icing code underline the need for a better understanding of the physics of wet ice growth.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 87-0178
    Format: text
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  • 19
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    Modeling of surface roughness effects on glaze ice accretion (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The cause and effects of roughness on accreting glaze ice surfaces were studied with microvideo observations. Distinct zones of surface water behavior were observed, including a smooth wet zone in the stagnation region with a uniform water film, a rough zone where surface tension effects caused coalescence of surface water into stationary beads, and a zone where roughness elements grow into horn shapes. In addition, a zone where surface water ran back as rivulets and a dry zone where rime feathers formed were observed. The locations and behaviors of these zones are discussed. A simple multizone modification to the glaze ice accretion model is proposed to include spatial variability in surface roughness. Two test cases using the multizone model showed significant improvements for the prediction of glaze ice shapes.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 89-0734
    Format: text
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  • 20
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    Investigation of surface water behavior during glaze ice accretion (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of experimental investigations that focused on isolating the primary factors that control the behavior of unfrozen surface water during glaze ice accretion were conducted. Detailed microvideo observations were made of glaze ice accretions on 2.54 cm diam cylinders in a closed-loop refrigerated wind tunnel. Distinct zones of surface water behavior were observed; a smooth wet zone in the stagnation region with a uniform water film, a rough zone where surface tension effects caused coalescence of surface water into stationary beads, and a zone where surface water ran back as rivulets. The location of the transition from the smooth to the rough zone was found to migrate towards the stagnation point with time. Comparative tests were conducted to study the effect of the substrate thermal and roughness properties on ice accretion. The importance of surface water behavior was evaluated by the addition of a surface tension reducing agent to the icing tunnel water supply, which significantly altered the accreted glaze ice shape. Measurements were made to determine the contact angle behavior of water droplets on ice. A simple multizone modification to current glaze ice accretion models was proposed to include the observed surface roughness behavior.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA, Langley Research Center, Joint University Program for Air Transportation Research, 1988-1989; p 55-62
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