Numerical Modeling Application for Studying the Water Content Field in Solving the Flight Safety Ensuring Problem for the Transport Category Aircraft under Conditions of Icing

Aeronautical and Space-Rocket Engineering


Аuthors

Berezko M. E.1, 2*, Okulov M. K.1, 2**, Shevyakov V. I.1***

1. Yakovlev Corporation Regional Aircraft Branch, 26, Leninskaya Sloboda str., Moscow, 115280, Russia
2. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: maxberezko@yandex.ru
**e-mail: owen99@mail.ru
***e-mail: shevvi@mail.ru

Abstract

The problem of aircraft surface icing has been a topic of scientific discussion and research for a long time. The ice growths forming on the wing and tail leads to a significant increase in drag and noticeable maximum values degradation of the aircraft lift and control efficiency. Besides accumulating on the load-bearing surfaces, the ice deposits may as well form on the air data system sensors, and affect negatively their operation. All these factors are being assessed as potentially dangerous consequences of getting under icing conditions inflight.
Both in Russia and abroad, works on studying icing conditions, types of ice deposits, their possible shapes and sizes, as well as the consequences arising from the ice forming on the aircraft surface and its elements are actively underway.
In the process of solving the problems of aerodynamics concerning the issue of icing computational fluid dynamics software is actively employed.
As of today, one of the program codes validation problems problems for their full-fledged application for flight safety ensuring of the transport category aircraft under icing conditions is insufficiently complete database of experiments and flight data conserning local liquid-water content (LWC) and conditions of undercooled large-drop icing (NLG-25 Appendix O).
The presented article solves the problem of relative LWC determining near the wing dynamic airfoil (in the 2D formulation) and near the fuselage nose part of the transport category aircraft. In view of the lack of the experimental data for validation, cross-verification of the FlowVision and FENSAP-ICE CDF-batches was performed.
On the assumption of the numerical modeling results, it can be stated that the FlowVision software can be applied for the task of the flight safety ensuring of the transport category aircraft under icing condition, but only under condition of the bundled software validation.
For further improvement of the two-phase flows modeling methods, the presence of validation base, concerning the bodies flow-around by the airflow under “standard” icing conditions, and particularly under conditions of the undercooled large-drop icing, including the liquid water distribution near the flown-around body, is urgent.

Keywords:

transport category aircraft, icing conditions, liquid water content, numerical modeling, CFD, FlowVision, FENSAP-ICE, Over-Concentration coefficient

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