Analysis of some numerical methods for studying aerodynamic interference
DOI:
https://doi.org/10.54858/dndia.2024-20-17Keywords:
aerodynamics, interference, wing, fuselage, power plant, geometric parameters, aircraft layout, viscosity of the medium, boundary layerAbstract
The results of the analysis of some numerical methods, which can be used in the modeling of aerodynamic interference at the stage of the preliminary design of the aircraft, are presented. Using the results of this analysis will speed up the selection of the most appropriate methods that allow simulating the airframe and its working engines with the same accuracy. The study of the modern methodology of numerical modeling of the flow around an aircraft of a complete layout will allow to identify the peculiarities of interference airframe and power plant elements.
The use of the methodological approaches proposed in the article will make it possible to determine the optimal layout of the aircraft in the formulation of the “wing-fuselage-engine” on the results of the achieved total aerodynamic characteristics.
Analyzes of modem armed conflicts shows that in most cases, the use of aviation has a decisive influence on the outcome of the conformation. Considering this, the main direction for the development of state aviation in Ukraine in the long term, with regard to the renewal of the military transport aviation fleet, is the design and production of advanced aircraft. Today, the world’s leading aircraft manufacturing companies (Airbus, Boeing and others) are working on the creation of competitive aircraft, which are based on conceptually new schemes. This is explained by the fact that the optimization of the shape of the aircraft can improve the performance by only a fraction of a percent, and changes in the layout of the aircraft can lead to more significant positive changes in these characteristics. Aerodynamic interference between the components of a certain layout of the design scheme of the designed aircraft is relatively large, and even minor changes in the geometry of one of the parts can significantly affect the overall aerodynamic characteristics of the aircraft. It is especially important at the stage of aircraft design to investigate the interference of working engines and airframe at different stages of flight.
The purpose of the article is to present the results of the analysis of some approaches and methods that can be used in modeling aerodynamic interference, which is important in determining the total aerodynamic characteristics of advanced aircraft at the design stage. This article proposes such research methods (methodologies):
- proven computational methods for optimizing the shape of an aircraft at the initial design stage;
- are also called methods of hydrodynamic singularities;
- are used to study aerohydrodynamics based on various combinations of distributed and discrete hydrodynamic features;
- calculate the bearing and moment characteristics of the profile in the framework of an ideal fluid; calculations based on the Navier-Stokes equations with a set of turbulence models that are used for more complete and reliable information for calculating the bearing and moment characteristics of the airfoil;
- not considered separately from each other, but together;
- method with subsequent solution of the boundary layer equations is used to take into account the effect of viscosity on the aerodynamic characteristics of the airfoil.
Conclusion: For solving problems of aerodynamic interference, of the ideal fluid model, the most suitable are the numerical-analytical and panel methods. More complete and reliable information on the calculation of the bearing and moment characteristics of the airfoil can be obtained by solving the full Navier-Stokes equations with a set of turbulence models. For those cases when it is necessary to obtain the aerodynamic characteristics of an aircraft that is designed with high accuracy, it is advisable to experimentally determine the corrections that are associated with the influence of operating engines.
References
Woodward F.A. A high order supersonic triplet singularity. – AIAA Paper, 1986, N 1815.
Rubin T.D. LOPAN-A low-order panel method for subsonic and supersonic flow // Aeronautical J. – May, 1989.
ЦАГИ основные этапы научной деятельности 1993-2003, под ред. доктора Дмитриева В.Г. – М.: ФИЗМАТЛИТ, 2003. – 576 с.
Jameson A., Schmidt W., Turkel E. Numerical solution of the Euler equations by finite volume methods using Runge-Kutta time-stepping scheme. AIAA-81-1259, June, 1981.
Годунов С.К., Забродин А.В., Иванов М.Я., Крайко А.Н., Прокопов Г.П. Численное решение многомерных задач газовой динамики. – М.: Наука, 1976. – 401 с.
Дегтярин В.Ф. Основы аэрогидрогазодинамики: учебное пособие. – Кировоград: ГЛАД, 2006. – 192 с.
Chi X. CFD Analysis of the Aerodynamics of a Business – Jet Airfoil with Leading – Edge Ice Accretion / X. Chi, B. Zhu, H.E. Addy // Reno, Nevada, 42 nd Aerospace Meeting and Exhibit. – 5-8 January 2004.
Adam P. Thermal and chemical non-equilibrium Navier-Stokes solver, TINA. Technical Report ESA-ESTEC EWP-1724, YPA, August, 1993.
Malouin B., Gariėpy M., Trėpanier J.-Y., Laurendeau Ė. İnstallation and interference drag decomposition via RANS far-field methods. Aerosp. Sci. Technol., 2016, vol. 54, pp. 132 – 142.
David W., Levy Data Summary and Comparison, AIAA CFD Drag Prediction Workshop, June, 2001. – p. 16.
Bosniakov S., Fonov S., Jitenev V., Shenkin F., Vlasenko V. and Yatskevich N. Method for Noise Suppressing Nozzle Calculation and First Result of Its Implementation, Jornal of Propulsion and Power, v. 14, № 1, January – February, 1998. – p. 101 – 109.
Репик Е.У. Приближенный расчет турбулентного пограничного слоя в сжимаемой жидкости при наличии градиента давления. М.: Журнал технической физики, т. ХХVІІ, вып. 2, 1957. – С. 744 – 752.
Репик Е.У. Исследование турбулентного пограничного слоя. “Труды ЦАГИ”, 1965, вып. 972.
– С. 3 – 41.
Ferziger J.H. Computational Methods for Fluid Dynamics / J.H. Ferziger, M. Peric // Springer,
– p. 431.
Скоморохов С.И., Теперин Л.Л., Свириденко Ю.Н. Методы аэродинамического проектирования поверхности элементов летательных аппаратов с учетом особенностей местной интерференции. В книге “Проблемы создания перспективной авиационно-космической техники.” – М.: Физматлит. 2005. – 195 с.
Сушак М.Б., Калкаманов С.А., Заріцький О.В., Гоцак В.В. Оцінка впливу роботи реактивних двигунів на аеродинамічні характеристики літака для різних варіантів геометричних параметрів їх розміщення відносно крила // Зб. наук. праць НАКУ “ХАІ”, м. Харків, 2005. - Вип. № 41(2). - С. 30-38.
Сушак М.Б., Гоцак В.В. Про важливість аеродинамічно-обґрунтованого розміщення реактивних двигунів відносно крила літака на етапі його проєктування // Зб. наук. праць ХАІ, Харків, 2006. - Вип. № 4(47). - С. 39-45.
Сушак М.Б., Чигрин Р.М., Скляр О.І. Дослідження щодо компонування двигунів на літальному апараті // Зб. наук. праць Харківського університету Повітряних Сил ім. Івана Кожедуба, Харків, 2012 р. - Вип. № 3(31), - С. 84-89.
Сушак М.Б., Кушніренко О.В., Сиворакша Д.В., Дудник Т.Г. Моделювання аеродинамічної інтерференції при створенні перспективних літаків // Зб. наук. праць ДНДІ ВС ОВТ, Черкаси, 2021. - Том 14 № 4 (2022). - С. 135-142.
S. Bosniakov Experience in integrating CFD to the technology of testing models in wind tunnels, Progress in Aerospace Sciences 34, November, 1998. – p. 391-422.
Босняков С.М., Акинориев В.О., Власенко В.В., Глазков С.А., Горбушин А.Р., Кожан Е.В.,
Михайлов С.В. Использование методов вычислительной аэродинамики в экспериментальных работах. ЦАГИ. Математическое моделирование, 2011, № 23(11), – С. 65-98.
