cahtНаучный вестник МГТУ ГАCivil Aviation High Technologies2079-06192542-0119Moscow State Technical University of Civil Aviation (MSTU CA)10.26467/2079-0619-2026-29-2-106-120caht-2752Research ArticleМАШИНОСТРОЕНИЕMECHANICAL ENGINEERINGЧисленное исследование аэродинамики комбинации планера и соосного несущего винта вертолета на основе метода URANSNumerical study of helicopter airframe aerodynamics combined with coaxial main rotor using the URANS methodКонстантиновС. Г.KonstantinovS. G.

Константинов Сергей Геннадьевич, кандидат технических наук, доцент кафедры проектирования вертолетов

г. Москва 

Sergey G. Konstantinov, Candidate of Technical Sciences, Associate Professor, Associate Professor, the Design and Certification of Aviation Equipment Chair

Moscow 

slk.konstantinov@gmail.comМакеевП. В.MakeevP. V.

Макеев Павел Вячеславович, доктор технических наук, доцент, профессор кафедры проектирования вертолетов

г. Москва 

Pavel V. Makeev, Doctor of Technical Sciences, Associate Professor, Associate Professor, the Design and Certification of Aviation Equipment Chair

Moscow 

makeevpv@mai.ruШомовА. И.ShomovA. I.

Шомов Александр Иванович, кандидат технических наук, доцент, доцент кафедры проектирования вертолетов

г. Москва 

Alexander I. Shomov, Candidate of Technical Sciences, Associate Professor, Associate Professor, the Design and Certification of Aviation Equipment Chair

Moscow 

shomov_aleksandr@mail.ruМосковский авиационный институт (национальный исследовательский университет)РоссияMoscow Aviation Institute (National Research University)Russian Federation202605052026292106120Copyright © Константинов С.Г., Макеев П.В., Шомов А.И., 20262026Константинов С.Г., Макеев П.В., Шомов А.И.Konstantinov S.G., Makeev P.V., Shomov A.I.Данная работа распространяется под лицензией Creative Commons Attribution 4.0.This work is licensed under a Creative Commons Attribution 4.0 License.https://avia.mstuca.ru/jour/article/view/2752

Работа посвящена численному моделированию аэродинамических характеристик планера вертолета Камов Ка-226, а также комбинации планера и соосного несущего винта. Использован метод CFD (computational fluid dynamics) на основе подхода URANS (Unsteady Reynolds-averaged Navier-Stokes equations) с моделью турбулентности k-ω SST на базе пакета Ansys Fluent. Созданная для решения поставленных задач гибридная оверсетная расчетная сетка содержала от 45 миллионов (планер) до 58 миллионов (комбинация планера и несущего винта) ячеек. Характеристики планера вертолета рассчитаны для различных конфигураций, таких как изолированный фюзеляж, фюзеляж + оперение, фюзеляж + оперение + колонка автомата перекоса, фюзеляж + оперение + колонка автомата перекоса + шасси (полная конфигурация) в диапазоне углов атаки планера от −16 до +16°. Комбинация планера и несущего винта рассчитана в полной конфигурации для скорости полета 30 м/c. Сравнение расчетных аэродинамических характеристик изолированного фюзеляжа и планера вертолета в полной конфигурации с экспериментальными данными продувок в аэродинамической трубе показало удовлетворительное совпадение. Результаты численного моделирования аэродинамических характеристик планера продемонстрировали ряд особенностей: возникновение отрицательной подъемной силы на фюзеляже на режиме горизонтального полета и формирование за ним двух мощных вихревых жгутов, оказывающих влияние на хвостовое оперение. Результаты численного моделирования аэродинамических характеристик комбинации планера и НВ позволили оценить также влияние вихревого следа НВ на аэродинамические характеристики планера. Выполненное исследование демонстрирует широкие возможности примененного подхода URANS для решения задач оптимизации аэродинамики вертолета с учетом интерференции его планера, отдельных частей и соосного несущего винта.

The work is dedicated to numerical modeling of Kamov Ka-226 helicopter aerodynamics for isolated helicopter airframe and helicopter airframe with coaxial main rotor. The CFD (computational fluid dynamics) method based on the URANS approach (Unsteady Reynolds-averaged Navier-Stokes equations) based on the Ansys Fluent software has been used. The hybrid overset mesh contained from 45 (isolated airframe) to 58 (airframe/rotor combination) million cells. The isolated helicopter airframe aerodynamic characteristics have been investigated for various airframe configurations such as: isolated fuselage, fuselage + tail, fuselage + tail + rotor head and fuselage + tail + rotor hub + landing gear (full configuration). The range of pitch angles from −16 to +16° has been considered. The full airframe/rotor combination aerodynamics has been investigated for a flight speed of 30 m/s. Comparison of calculated aerodynamic characteristics of isolated fuselage and full airframe configuration with wind tunnel (WT) test data has showed a satisfactory match. The results of numerical modelling of helicopter airframe aerodynamics have demonstrated specific features, such as: presence of negative lift force on the helicopters fuselage in horizontal flight and formation of two powerful vortex bundles behind the fuselage that affecting the tail stabilizer. The results of numerical modelling of helicopter airframe/rotor combination have allowed evaluating the effect of main rotor wake on the helicopter airframe aerodynamics. The performed study demonstrates the wide possibilities of the URANS approach in solving the complex problems of optimizing helicopter aerodynamics, taking into account the interference of airframe, its individual parts and main rotor.

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The authors declare that there are no conflicts of interest present.