Icing Certification of Korean Utility Helicopter KUH-1: Artificial Icing Flight Test

Hoff, Stefan van 't; Vorst, J. van der; Flemming, Robert J.; Parkins, David

doi:10.2514/6.2017-3930

Cited by 5 publications

(2 citation statements)

References 1 publication

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“…Hence, it is possible to obtain SLD conditions by running a single auxiliary power unit to lower the humidity. In the experiments, Netherlands Aerospace Centre managed to get the drop size distribution, as shown in Figure 5 [27], where the MVD is over 40 μm.…”

Section: 5ch-47dmentioning

confidence: 99%

Sustainable future for icing tankers in civil aviation certification

Wu,

Ni,

Wang

et al. 2024

E3S Web of Conf.

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This document summarizes the regulations of civil aviation in terms of icing certifications, and how they affect the flight tests process. To certify a fully new designed aircraft or eVTOLs, chasing the natural icing conditions defined in the regulations is time consuming and pricey, which could be a burden for startup smart transportation companies. Over the years, icing tankers have been built and simulated icing conditions to verify and validate the wind tunnel and computational results. With nozzle arrays controlled by computers, icing tankers simulating and substituting natural icing conditions flight will be a potential way to minimize the certification process.

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Section: 5ch-47dmentioning

confidence: 99%

Sustainable future for icing tankers in civil aviation certification

Wu,

Ni,

Wang

et al. 2024

E3S Web of Conf.

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“…In addition, the expenditure of the flight test is very high. Compared to the natural icing test, airborne tanker 24 is a relatively better way to achieve a prescribed icing condition. The test helicopter can fly in an artificial cloud produced by the tanker aircraft.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation on the performance degradation of helicopter rotor due to ice accretion

Huang

Yuan

Wang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Helicopter rotor performance can be significantly altered by ice accretion which directly degrades the handling qualities and safety during flight. To obtain understanding into the effect of ice accretion on a helicopter rotor in forward flight under different icing environments, an experimental campaign was conducted in an icing wind tunnel using a rotor model with diameter at 2 m. Research was emphasized on revealing effect of liquid water content and static temperature on the rotor performance degradation. The dynamic thrust and torque of the rotor were measured by a six-component balance. Ice shape of the airfoils at specific rotor blade spanwise locations was obtained through the ice cutting process; meanwhile, the entire ice topology on the blade was scanned by means of the three-dimensional scanning technique. Results showed that ice was mainly accreted on the leading edge and lower surface of the blade. The static temperature of a icing cloud has a noticeable effect on the regime of accreted ice. The ice formation was transparent glaze at −8°C and transformed to milky rime when changed the static temperature to −20°C. Comparing to rime ice, the glaze ice on the blade is more influential to the rotor performance degradation. Particular attention is given to the fact that under extreme icing conditions, over 30% degradation of transient rotor thrust was observed.

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Numerical Simulation and Meta Model of Rotorcraft Electrothermal Ice Protection Systems

Myong

Jung²

2023

Handbook of Numerical Simulation of in-Flight Icing

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Icing Certification of Korean Utility Helicopter KUH-1: Artificial Icing Flight Test

Cited by 5 publications

References 1 publication

Sustainable future for icing tankers in civil aviation certification

Sustainable future for icing tankers in civil aviation certification

Experimental investigation on the performance degradation of helicopter rotor due to ice accretion

Numerical Simulation and Meta Model of Rotorcraft Electrothermal Ice Protection Systems

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