Experimental investigation on the icing physics and anti-/de-Icing technology of an aircraft pitot probe

dc.contributor.advisor Hui Hu
dc.contributor.author Al-Masri, Faisal
dc.contributor.department Aerospace Engineering
dc.date 2021-01-16T18:18:22.000
dc.date.accessioned 2021-02-25T21:37:37Z
dc.date.available 2021-02-25T21:37:37Z
dc.date.copyright Tue Dec 01 00:00:00 UTC 2020
dc.date.embargo 2020-11-27
dc.date.issued 2020-01-01
dc.description.abstract <p>Pitot probes are one of the most important components of an airplane, directly responsible for the flight safety and secure decisions of pilots by providing crucial airspeed and altitude data. They are constantly at risk of performance deterioration due to ice accretion that can block the stagnation port, thereby, providing incorrect readings to the pilot that can lead to fatal accidents if not treated immediately. By leveraging the unique Icing Research Tunnel at Iowa State University (i.e., ISU-IRT) a series of experimental studies are conducted to investigate the dynamic ice accretion process over the surface of a commonly-used aircraft pitot probe and to evaluate the effectiveness of various anti-/de-icing methods for Pitot probe icing mitigation. During the experiments, in addition to using a high-resolution imaging system to record the dynamic ice accretion and anti-/de-icing processes over the surface of the Pitot probe under different icing test conditions, a high-speed Infrared (IR) thermal imaging system is also used to map the corresponding surface temperature distributions on the Pitot probe in order to characterize the unsteady heat transfer process associated with the ice accretion and anti-/de-icing process. In addition to performing a parametric study to evaluate the performance of a conventional thermal-based icing protection system embedded inside the Pitot-probe as a function of the electric power input for the anti-/de-icing operation, a novel hybrid icing protection strategy is proposed that combines the electric heating with a bio-inspired superhydrophobic (SHS) coating to coat the Pitot probe in order to minimize the power consumption for the anti-/de-icing operation. In comparison to that required by the conventional thermal-based system to heat up the Pitot probe brutally for icing protection, the proposed hybrid strategy is found to be able to achieve completely ice free conditions over the entire surface of the Pitot probe with only about 35% of the required power input (i.e., up to 65% power consumption) for the anti-/de-icing operation.</p>
dc.format.mimetype application/pdf
dc.identifier archive/lib.dr.iastate.edu/etd/18269/
dc.identifier.articleid 9276
dc.identifier.contextkey 21104678
dc.identifier.doi https://doi.org/10.31274/etd-20210114-4
dc.identifier.s3bucket isulib-bepress-aws-west
dc.identifier.submissionpath etd/18269
dc.identifier.uri https://dr.lib.iastate.edu/handle/20.500.12876/94421
dc.language.iso en
dc.source.bitstream archive/lib.dr.iastate.edu/etd/18269/AlMasri_iastate_0097M_19152.pdf|||Fri Jan 14 21:39:24 UTC 2022
dc.subject.keywords De-Icing
dc.subject.keywords Icing
dc.title Experimental investigation on the icing physics and anti-/de-Icing technology of an aircraft pitot probe
dc.type article
dc.type.genre dissertation
dspace.entity.type Publication
relation.isOrgUnitOfPublication 047b23ca-7bd7-4194-b084-c4181d33d95d
thesis.degree.discipline Aerospace Engineering
thesis.degree.level dissertation
thesis.degree.name Master of Science
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