Improvement of aerodynamic characteristics of a thick airfoil with a vortex cell in sub- and transonic flow

Исаев, С. А.; Baranov, P. A.; Попов, И. А.; Sudakov, A. G.; Usachov, A. E.

doi:10.1016/j.actaastro.2016.11.029

Cited by 14 publications

(9 citation statements)

References 32 publications

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“…The wind tunnel testing technology is the most effective and reliable way of obtaining the aerodynamic characteristics of aircrafts [28,29], spacecrafts [30], missiles, parachutes and so on. During the experiments, the total pressure and the temperature were kept at 110KPa and 287K, respectively.…”

Section: Resultsmentioning

confidence: 99%

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Dong¹,

Yang²,

Yu³

et al. 2018

dtcse

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An experimental study is conducted to characterize the aerodynamic performances of two parachutes in the Mars probe decelerator system and the experiments are carried out in the 2.4 m×2.4 m transonic wind tunnel. The lift, drag and pitch moment coefficients versus the angle of attack from 0 to 25 degrees at Mach 0.4 and 0.8 are accurately measured and carefully analyzed. A novel mathematical model is proposed to express the aerodynamic characteristics of the parachutes. The obtained results show that the drag coefficient of the parachutes varies in a small range of 0.525~0.575 at Mach 0.4 and 0.8 as the angle of attack increases from 0 to 25 degrees. The simulated results of the propose model have a well agreement with the wind tunnel experimental data. The investigations in the present paper have a good significant to the engineering development of the parachutes in Mars probe decelerator system.

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Section: Resultsmentioning

confidence: 99%

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Dong¹,

Yang²,

Yu³

et al. 2018

dtcse

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“…All these parameters can be noted as the dynamic parameters. Solving equations (10) and (12), the parameters can be gained by the nonlinear least square method and the obtained values of the parameters are related with the selected initial values. Different initial values may lead to different obtained parameters.…”

Section: Parameter Identification Methodsmentioning

confidence: 99%

“…In the flight simulations and aircraft design, the accuracy predictions of the aerodynamic forces and moments are required. 9–12 A number of the investigations on that topic have been published. 13–16 Early in 1975, the static aerodynamic characteristics of F-4D fighter airplane was modeled by Monfort et al.…”

Section: Introductionmentioning

confidence: 99%

“…7,8 In the flight simulations and aircraft design, the accuracy predictions of the aerodynamic forces and moments are required. [9][10][11][12] A number of the investigations on that topic have been published. [13][14][15][16] Early in 1975, the static aerodynamic characteristics of F-4D fighter airplane was modeled by Monfort et al 17 Peterson et al 18 utilized a neural network to describe the aerodynamic parameters of F-15 SMTD (STOL (Short Take-off and Landing) and Maneuver Technology Demonstrator) aircraft.…”

Section: Introductionmentioning

confidence: 99%

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Modeling of unsteady aerodynamic characteristics at high angles of attack

Dong

Zhang

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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An improved model to express the unsteady aerodynamic characteristics at high angles of attack is presented in this paper. The proposed aerodynamic model is expressed on the basis of a progressive state-space representation and Taylor’s series expansion. The state-space expression is a first-order differential equation in which the power item of the angular rate of attack is introduced. The unsteady aerodynamic coefficients are described by Taylor’s series expansion in terms of input variables. The approach of minimum mean square error criterion is utilized to identify the unknown parameters of the proposed model by nonlinear least square method from the tunnel data. The given modeling method is experimentally demonstrated by the wind tunnel measurements of NACA 0015 airfoil with constant rate to high angles of attack, F18 aircraft with constant pitch rate ramp motion, and F18 HARV (high alpha research vehicle) configuration with large-amplitude harmonic oscillatory. The results show that it is possible to analyze more complex unsteady aerodynamic problems for an aircraft within the framework of the proposed aerodynamic model and the represented model is directly amenable to the simulation and control system design.

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“…В [3] показано, что щелевой отсос из эллиптических вихревых ячеек позволяет уменьшить лобовое сопротив-ление профиля ЛА ЭКИП и увеличить его аэродинамическое качество. Круговые формы малогабаритных вихревых ячеек со щелевым отсосом анализируются в [4,5] для толстых профилей классической формы.…”

Section: поступило в редакцию 10 июля 2017 гunclassified

Управление Обтеканием Полукругового Профиля Под Нулевым Углом Атаки При Отсосе В Одной И Двух Вихревых Ячейках Для Достижения Экстремальной Подъемной Силы

Исаев¹,

Баранов²,

Судаков³

et al. 2017

Письма В Журнал Технической Физики

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На основе расчетов с помощью многоблочных вычислительных технологий и модифицированной с учетом влияния кривизны линий тока модели переноса сдвиговых напряжений турбулентного обтекания полукругового профиля под нулевым углом атаки с расположенными на контуре одной и двумя вихревыми ячейками со щелевым отсосом обнаружены стабилизация близкого к безотрывному течения и достижение экстремального коэффициента подъемной силы Cy = 5.2 и аэродинамического качества K = 24 профиля с учетом энергетических потерь на отсос в ячейках. DOI: 10.21883/PJTF.2017.24.45341.16961

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Improvement of aerodynamic characteristics of a thick airfoil with a vortex cell in sub- and transonic flow

Cited by 14 publications

References 32 publications

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Modeling of unsteady aerodynamic characteristics at high angles of attack

Управление Обтеканием Полукругового Профиля Под Нулевым Углом Атаки При Отсосе В Одной И Двух Вихревых Ячейках Для Достижения Экстремальной Подъемной Силы

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