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  • 1
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    Wind Tunnel Measured Effects on a Twin-Engine Short-Haul Transport Caused by Simulated Ice Accretions: Data Report (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this report is to release the data from the NASA Langley/Lewis 14 by 22 foot wind tunnel test that examined icing effects on a 1/8 scale twin-engine short-haul jet transport model. Presented in this document are summary data from the major configurations tested. The entire test database in addition to ice shape and model measurements is available as a data supplement in CD-ROM form. Data measured and presented are: wing pressure distributions, model force and moment, and wing surface flow visualization.
    Keywords: Air Transportation and Safety
    Type: NASA-TM-107419 , NAS 1.15:107419 , E-10659
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    National Transportation Safety Board Aircraft Accident Investigation Supported (1999)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: The main purpose of this investigation was for NASA to help the National Transportation Safety Board (NTSB) gain better understanding of the events that led to the loss of Comair Flight 3272 over Monroe, Michigan, on January 9, 1997. In-flight icing was suspected as being the primary cause of this accident. Of particular interest to the Safety Board was what NASA could learn about the potential performance degradation of the wing of the Embraer EMB-120 twin-turboprop commuter aircraft with various levels of ice contamination. NASA agreed to undertake (1) ice-accretion prediction computations with NASA s LEWICE program to bound the kind of contaminations that the vehicle may have developed, (2) testing in the NASA Lewis Research Center's Icing Research Tunnel to verify and refine the ice shapes developed by LEWICE, (3) a two-dimensional Navier- Stokes analysis to determine the performance degradation that those ice shapes could have caused, and (4) an examination using three-dimensional Navier-Stokes codes to study the three-dimensional effects of ice contamination.
    Keywords: Air Transportation and Safety
    Type: Research and Technology 1998; NASA/TM-1999-208815
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Wind Tunnel Measured Effects on a Twin-Engine Short-Haul Transport Caused by Simulated Ice Accretions (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A series of wind tunnel tests were conducted to assess the effects of leading edge ice contamination upon the performance of a short-haul transport. The wind tunnel test was conducted in the NASA Langley 14 by 22 foot facility. The test article was a 1/8 scale twin-engine short-haul jet transport model. Two separate leading edge ice contamination configurations were tested in addition to the uncontaminated baseline configuration. Several aircraft configurations were examined including various flap and slat deflections, with and without landing gear. Data gathered included force measurements via an internal six-component force balance, pressure measurements through 700 electronically scanned wing pressure ports, and wing surface flow visualization measurements. The artificial ice contamination caused significant performance degradation and caused visible changes demonstrated by the flow visualization. The data presented here is just a portion of the data gathered. A more complete data report is planned for publication as a NASA Technical Memorandum and data supplement.
    Keywords: Air Transportation and Safety
    Type: NASA-TM-107143 , AIAA Paper 96-0871 , E-10073 , NAS 1.15:107143 , Aerospace Sciences Meeting and Exhibit; Jan 15, 1996 - Jan 18, 1996; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Wind Tunnel Measured Effects on a Twin-Engine Short-Haul Transport Caused by Simulated Ice Accretions: Data Report (1997)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The purpose of this report is to release the data from the NASA Langley/Lewis 14 by 22 foot wind tunnel test that examined icing effects on a 1/8 scale twin-engine short-haul jet transport model. Presented in this document are summary data from the major configurations tested. The entire test database in addition to ice shape and model measurements is available as a data supplement in CD-ROM form. Data measured and presented are: wing pressure distributions, model force and moment, and wing surface flow visualization.
    Keywords: Air Transportation and Safety
    Type: NASA-TM-107419 , E-10659
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Aircraft Icing Weather Data Reporting and Dissemination System (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The long-term operational concept of this research is to develop an onboard aircraft system that assesses and reports atmospheric icing conditions automatically and in a timely manner in order to improve aviation safety and the efficiency of aircraft operations via improved real-time and forecast weather products. The idea is to use current measurement capabilities on aircraft equipped with icing sensors and in-flight data communication technologies as a reporting source. Without requiring expensive avionics upgrades, aircraft data must be processed and available for downlink. Ideally, the data from multiple aircraft can then be integrated (along with other real-time and modeled data) on the ground such that aviation-centered icing hazard metrics for volumes of airspace can be assessed. As the effect of icing on different aircraft types can vary, the information should be displayed in meaningful ways such that multiple types of users can understand the information. That is, information must be presented in a manner to allow users to understand the icing conditions with respect to individual concerns and aircraft capabilities. This research provides progress toward this operational concept by: identifying an aircraft platform capable of digitally capturing, processing, and downlinking icing data; identifying the required in situ icing data processing; investigating the requirements for routing the icing data for use by weather products; developing an icing case study in order to gain insight into major air carrier needs; developing and prototyping icing display concepts based on the National Center for Atmospheric Research's existing diagnostic and forecast experimental icing products; and conducting a usability study for the prototyped icing display concepts.
    Keywords: Air Transportation and Safety
    Type: NASA/CR-2002-211800 , E-13495 , NAS 1.26:211800
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Comparison of Profiling Microwave Radiometer, Aircraft, and Radiosonde Measurements From the Alliance Icing Research Study (AIRS) (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Measurements from a profiling microwave radiometer are compared to measurements from a research aircraft and radiosondes. Data compared is temperature, water vapor, and liquid water profiles. Data was gathered at the Alliance Icing Research Study (AIRS) at Mirabel Airport outside Montreal, Canada during December 1999 and January 2000. All radiometer measurements were found to lose accuracy when the radome was wet. When the radome was not wetted, the radiometer was seen to indicate an inverted distribution of liquid water within a cloud. When the radiometer measurements were made at 15 deg. instead of the standard zenith, the measurements were less accurate.
    Keywords: Air Transportation and Safety
    Type: NASA/TM-2001-211101 , E-12946 , NAS 1.15:211101
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The Winter 2010 and 2011 FRONT/NIRSS In-Flight Icing Hazard Detection Project (2011)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The NASA Icing Remote Sensing System (NIRSS) deploys a vertically-pointing K-band radar, a lidar ceiliometer, and a profiling microwave radiometer to obtain measurements for diagnosing local inflight icing conditions. RAL is working with NASA GRC to develop algorithms and data ingest and display software for the system. NASA has an ongoing activity to develop remote sensing technologies for the detection and measurement of icing conditions aloft. As part of that effort NASA teamed with NCAR to develop software that fuses data from multiple instruments into a single detected icing condition product. The multiple instrument approach, which is the current emphasis of this activity, utilizes a K-band vertical staring radar, a microwave radiometer that detects twelve frequencies between 22 and 59 GHz, and a lidar ceilometer. The radar data determine cloud boundaries, the radiometer determines the sub-freezing temperature heights and total liquid water content, and the ceilometer refines the lower cloud boundary. Data is post-processed in C++ program with a Java-based web display of resultant supercooled LWC profile and aircraft hazard identification. In 2010, a multi-channel scanning radiometer, designed and built by Radiometrics, Inc. under a SBIR grant,,was added to the system to assess its utility in improving icing diagnoses.
    Keywords: Air Transportation and Safety
    Type: E-667820 , NASA Aviation Safety Annual Technical Meeting; May 10, 2011 - May 12, 2011; Saint Louis, MO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Comparison of In-Situ, Model and Ground Based In-Flight Icing Severity (2011)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Currently there are two systems that are being developed for the detection of in-flight icing: NASA Icing Remote Sensing System (NIRSS) and current Icing Product (CIP). In-flight icing (IFI) is a significant hazard for the aviation industry. IFI occurs when supercooled liquid water (SLW) comes in contact with, and freezes to, the leading surfaces of an aircraft. Significantly alters aircraft aerodynamic properties: increases the amount of drag on an aircraft and reduces the lift. The objective of this study is to examine how the testbed NIRSS icing severity product and the operational CIP severity product compare to PIREPs of icing severity, and how the NIRSS and CIP compare to each other.
    Keywords: Air Transportation and Safety
    Type: E-667819 , Aviation Safety Program Annual Technical Meeting; May 10, 2011 - May 12, 2011; St. Louis, MO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Comparison of In-Situ, Model and Ground Based In-Flight Icing Severity (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: As an aircraft flies through supercooled liquid water, the liquid freezes instantaneously to the airframe thus altering its lift, drag, and weight characteristics. In-flight icing is a contributing factor to many aviation accidents, and the reliable detection of this hazard is a fundamental concern to aviation safety. The scientific community has recently developed products to provide in-flight icing warnings. NASA's Icing Remote Sensing System (NIRSS) deploys a vertically--pointing Ka--band radar, a laser ceilometer, and a profiling multi-channel microwave radiometer for the diagnosis of terminal area in-flight icing hazards with high spatial and temporal resolution. NCAR s Current Icing Product (CIP) combines several meteorological inputs to produce a gridded, three-dimensional depiction of icing severity on an hourly basis. Pilot reports are the best and only source of information on in-situ icing conditions encountered by an aircraft. The goal of this analysis was to ascertain how the testbed NIRSS icing severity product and the operational CIP severity product compare to pilot reports of icing severity, and how NIRSS and CIP compare to each other. This study revealed that the icing severity product from the ground-based NASA testbed system compared very favorably with the operational model-based product and pilot reported in-situ icing.
    Keywords: Air Transportation and Safety
    Type: NASA/TM-2011-217141 , Paper No. 10.2 , E-17878 , 15th Symposium on Integrated Observing and Assimilation Systems for the Atmosphere, Oceans, and Land Surface (IOAS-AOLS); Jan 27, 2011; Seattle, WA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Preliminary Analysis of X-Band and Ka-Band Radar for Use in the Detection of Icing Conditions Aloft (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA and the U.S. Army Cold Regions Research and Engineering Laboratory (CRREL) have an on-going activity to develop remote sensing technologies for the detection and measurement of icing conditions aloft. Radar has been identified as a strong tool for this work. However, since the remote detection of icing conditions with the intent to identify areas of icing hazard is a new and evolving capability, there are no set requirements for radar sensitivity. This work is an initial attempt to quantify, through analysis, the sensitivity requirements for an icing remote sensing radar. The primary radar of interest for cloud measurements is Ka-band, however, since NASA is currently using an X-band unit, this frequency is also examined. Several aspects of radar signal analysis were examined. Cloud reflectivity was calculated for several forms of cloud using two different techniques. The Air Force Geophysical Laboratory (AFGL) cloud models, with different drop spectra represented by a modified gamma distribution, were utilized to examine several categories of cloud formation. Also a fundamental methods approach was used to allow manipulation of the cloud droplet size spectra. And an analytical icing radar simulator was developed to examine the complete radar system response to a configurable multi-layer cloud environment. Also discussed is the NASA vertical pointing X-band radar. The radar and its data system are described, and several summer weather events are reviewed.
    Keywords: Air Transportation and Safety
    Type: NASA/TM-2004-212901 , AIAA Paper 2004-0233 , E-14318 , 42nd Aerospace Sciences Meeting and Exhibit; Jan 05, 2004 - Jan 08, 2004; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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