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A review of droplet sizing instruments used for icing research is presented. These instruments include the Forward Scattering Spectrometer Probe, the Optical Array Probe, the Phase Doppler Particle Analyzer, the Malvern Particle Size Analyzer, the oil slide technique, and the rotating multicylinder. The report focuses on the theory of operation of these instruments and practical considerations when using them in icing facilities.

This SAE Aerospace Information Report (AIR) presents and discusses the results of tests of three models in six icing wind tunnels in North America and Europe. This testing activity was initiated by the Facility Standardization Panel of the SAE AC-9C Aircraft Icing Technology Subcommittee. The objective of the testing activity was to establish a benchmark that compared ice shapes produced by icing wind tunnels available for use by the aviation industry and to use that benchmark as a basis for dialogue between facility owners to improve the state-of-the-art of icing wind tunnel technology.

This SAE Aerospace Information Report (AIR) presents and discusses the results of tests of three models in six icing wind tunnels in North America and Europe. This testing activity was initiated by the Facility Standardization Panel of the SAE AC-9C Aircraft Icing Technology Subcommittee. The objective of the testing activity was to establish a benchmark that compared ice shapes produced by icing wind tunnels available for use by the aviation industry and to use that benchmark as a basis for dialogue between facility owners to improve the state-of-the-art of icing wind tunnel technology.

This SAE Aerospace Information Report (AIR) contains information on most of the major icing simulation ground facilities. An effort was made to obtain data from as many facilities as possible over a two year time period. The data in this document represents the state of the facilities in calendar year 1996. Facilities are constantly changing and upgrading and, therefore, some facility specifications may change during the life of this report. Of the 27 facilities described in this report, the primary use is split with approximately half for engine testing and half for wind tunnel testing. The facilities are limited to ground facilities and, therefore, icing tankers have not been included.

This SAE Aerospace Information Report (AIR) contains information on most of the major icing simulation ground facilities. An effort was made to obtain data from as many facilities as possible over a two year time period. The data in this document represents the state of the facilities in calendar year 1996. Facilities are constantly changing and upgrading and, therefore, some facility specifications may change during the life of this report. Of the 27 facilities described in this report, the primary use is split with approximately half for engine testing and half for wind tunnel testing. The facilities are limited to ground facilities and, therefore, icing tankers have not been included.

This Aerospace Information Report (AIR) identifies and summarizes the various factors that should be considered during design, development, certification, or testing of helicopter rotor blade ice protection. Although various concepts of ice protection are mentioned in this report, the text is limited generally to those factors associated with design and substantiation of cyclic electrothermal ice protection systems as applicable to the protection of helicopter rotor blades. Other systems are described briefly in Appendix A. Applications consider main rotor blades, conventional tail rotor blades, and other types of antitorque devices. The information contained in this report is also limited to the identification of factors that should be considered and why the factor is important. Specific design, analysis and test methodologies are not included. For additional information refer to the references in Section 7.

This SAE Aerospace Information Report (AIR) identifies and summarizes the various factors that should be considered during design, development, certification, or testing of helicopter rotor blade ice protection systems. Although various concepts of ice protection are mentioned in this report, the text is limited generally to those factors associated with design and substantiation of cyclic electrothermal ice protection systems as applicable to the protection of helicopter rotor blades. Other systems are described briefly in Appendix A. Applications consider main rotor blades, conventional tail rotor blades, and other types of antitorque devices. The information contained in this report is also limited to the identification of factors that should be considered and why the factor is important. Specific design, analysis and test methodologies are not included. For additional information refer to the references listed in 2.1.

This SAE Aerospace Information Report (AIR) identifies and summarizes the various factors that should be considered during design, development, certification, or testing of helicopter rotor blade ice protection systems. Although various concepts of ice protection are mentioned in this report, the text is limited generally to those factors associated with design and substantiation of cyclic electrothermal ice protection systems as applicable to the protection of helicopter rotor blades. Other systems are described briefly in Appendix A. Applications consider main rotor blades, conventional tail rotor blades, and other types of antitorque devices. The information contained in this report is also limited to the identification of factors that should be considered and why the factor is important. Specific design, analysis and test methodologies are not included. For additional information refer to the references listed in 2.1.

This SAE Aerospace Information Report (AIR) provides a comprehensive overview of primary water content measurement instrumentation, for both facility-based icing research and in-flight icing research, over the range of commonly used aircraft certification icing envelopes. It includes information on the theory of operation of the instruments, system errors and limitations, and practical considerations when using them for cloud characterization. This document does not address other icing cloud measurements of interest, such as particle sizing, or measurement of phenomena such as snow, sleet, or hail.

This SAE Aerospace Recommended Practice (ARP) document provides recommended practices for the calibration and acceptance of icing wind tunnels to be used in testing of aircraft components and systems and for the development of simulated ice shapes. This document is not applicable to air-breathing propulsion test facilities configured for the purposes of engine icing tests. Use of facilities as part of an aircraft’s ice protection Certification Plan should be reviewed and accepted by the applicable regulatory agency prior to testing. Following acceptance of a test plan, data generated in these facilities may be submitted to regulatory agencies for use in the certification of aircraft ice protection systems and components. Certain types of tests may be appropriate in facilities with capabilities that are not as rigorously characterized as by the practices defined herein, and the acceptability of these tests should be coordinated with the applicable regulatory agency.

This SAE Aerospace Information Report (AIR) provides various graphical displays of atmospheric variables related to aircraft icing conditions in natural clouds. It is intended as a review of recent developments on the subject, and for stimulating thought on novel ways to arrange and use the available data. Included in this Report is FAR 25 (JAR 25) Appendix C, the established Aircraft Icing Atmospheric Characterization used for engineering design, development, testing and certification of civilian aircraft to fly in aircraft icing conditions.

This SAE Aerospace Information Report (AIR) provides various graphical displays of atmospheric variables related to aircraft icing conditions in natural clouds. It is intended as a review of recent developments on the subject, and for stimulating thought on novel ways to arrange and use the available data. Included in this Report is FAR 25 (JAR 25) Appendix C, the established Aircraft Icing Atmospheric Characterization used for engineering design, development, testing and certification of civilian aircraft to fly in aircraft icing conditions.

This SAE Aerospace Standard (AS) establishes minimum ice and rain performance criteria for electrically-heated pitot and pitot-static probes intended for use on the following classes of fixed-wing aircraft and rotorcraft. The classes of fixed-wing aircraft are defined by aircraft flight envelopes and are shown in Figure 1. The flight envelopes generally fall into the classes as shown below: The user of this standard must evaluate the aircraft level installation requirements for the probe against the class definition criteria to ensure adequate coverage for the application. It may be necessary to step up in class or modify the test conditions in order to meet the applicable installation requirements. NOTE: Class 2 is divided into two subgroups identified as either Class 2a or Class 2b. Class 2a probe applications typically include aircraft that operate within the mid to lower end of the Class 2 altitude range and that only use probe output to display basic airspeed and/or altitude.