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- W2316457592 abstract "A full-scale Lockheed Martin F-22 Raptor engine inlet and duct icing model was tested in the NASA Icing Research Tunnel to assess ice detector configurations and quantify ice accretion characteristics. Test conditions included temperatures from -4 to 28 degrees Fahrenheit, liquid water contents from 0.31 to 2.82 grams/cubic meter, and median volumetric diameters of 14 and 30 microns. The attitude, airspeed, and inlet airflows simulated landing approach conditions. An optimum ice detection configuration was selected from six candidates. The preferred configuration was a probetype ice detector located approximately three feet forward of the aerodynamic interface plane in the lower outboard section of the duct. Ice thickness on the inlet was measured. Accretion rates were derived from the measured ice thickness and compared to analytical predictions." @default.
- W2316457592 created "2016-06-24" @default.
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- W2316457592 date "1998-01-12" @default.
- W2316457592 modified "2023-09-23" @default.
- W2316457592 title "F-22 inlet and duct ice detection and accretion test" @default.
- W2316457592 doi "https://doi.org/10.2514/6.1998-572" @default.
- W2316457592 hasPublicationYear "1998" @default.
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