Response Surface Method Application to High-Lift Configuration with Active Flow Control

Vrchota, Petr; Hospodář, Pavel

doi:10.2514/1.c031624

Cited by 11 publications

(9 citation statements)

References 7 publications

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“…For that reason, a gradient method is used to inner optimization. As a design procedure a Response surface methodology (RSM) is used [8] in this work. It is simple and relatively widely used methodology in optimization problems [9].…”

Section: Optimization Of Wings Geometrymentioning

confidence: 99%

Comparison of aerodynamic characteristics provided by wing with bell shaped lift distribution and generalized wings

Hospodář

Drábek

2019

MATEC Web Conf.

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In this article different wings are computed by low and high-fidelity methods to compare their aerodynamic characteristics. Thanks to the unusual properties of the wing with the bell-shaped lift distribution, several general geometrical variants of the wings were calculated and their results are presented in this work. Three general wings are assumed and their geometry is defined as rectangular, trapezoidal and elliptical. Airspeed, total lift force, shape of airfoil and root chord are defined, and bending moment is assumed as a surrogate model for wing weight. The goal of optimization is minimization of aerodynamic drag.

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Section: Optimization Of Wings Geometrymentioning

confidence: 99%

Comparison of aerodynamic characteristics provided by wing with bell shaped lift distribution and generalized wings

Hospodář

Drábek

2019

MATEC Web Conf.

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“…A wide range of usage of surrogate modeling had been seen in the field of computational science in recent decades. There are many mathematical approaches that provide surrogate modeling: Kriging, Response surface method [6], artificial neural networks [29], Gaussian processes [30], and so on. In this case, an analytical function, describing the character of the flow field, was used.…”

Section: Definition Of the Boundary Conditionmentioning

confidence: 99%

“…It has become quite popular to control flows in many aeronautical, transport, and industrial applications [3][4][5]. A number of computational studies rely on a uniform flow field at the AFC device exit [6][7][8][9][10]. It is evident that a realistic jet exit flow field is needed, in order to define appropriate boundary conditions [2,11,12] and to obtain physically consistent interactions between the actuator and the outer flow.…”

Section: Introductionmentioning

confidence: 99%

Verification of Boundary Conditions Applied to Active Flow Circulation Control

2019

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Inclusion of Active Flow Control (AFC) into Computational Fluid Dynamics (CFD) simulations is usually highly time-consuming and requires extensive computational resources and effort. In principle, the flow inside of the fluidic AFC actuators should be incorporated into the problem under consideration. However, for many applications, the internal actuator flow is not crucial, and only its effect on the outer flow needs to be resolved. In this study, the unsteady periodic flow inside the Suction and Oscillatory Blowing (SaOB) actuator is analyzed, using two CFD methods of ranging complexity (URANS and hybrid RANS-LES). The results are used for the definition and development of the simplified surface boundary condition for simulating the SaOB flow at the actuator’s exit. The developed boundary condition is verified and validated, in the case of a low-speed airfoil with suction applied on the upper (suction) side of the airfoil and oscillatory blowing applied on the lower (pressure) side, close to the trailing edge—a fluidic Gurney flap. Its effect on the circulation is analyzed and compared to the experimental data.

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“…The fully modeled cavities have some drawback in terms of the grid creation, number of cells etc., but the flow at the cavities' outlets is more realistic. On the other hand same effort has been devoted to applying the surface boundary conditions simulating the flow from actuators and actuation models in the past [7,[9][10][11]. …”

Section: Boundary Conditions and Cfd Solvermentioning

confidence: 99%

“…A significant effort of experimental and numerical investigation of the application of the passive and AFC techniques to locally suppress the flow separation or improve the high-lift performances at the wing-pylon area, outer-wing or applied to high-lift devices has been done [3][4][5][6][7]. This paper summarized the results of the SJA of the high-lift configuration using the CFD simulation by means of URANS approach.…”

Section: Introductionmentioning

confidence: 99%

Application of Synthetic Jets Actuators in Wing-Pylon Junction Area to Improve the High Lift Performances

Vrchota¹

2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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Response Surface Method Application to High-Lift Configuration with Active Flow Control

Cited by 11 publications

References 7 publications

Comparison of aerodynamic characteristics provided by wing with bell shaped lift distribution and generalized wings

Comparison of aerodynamic characteristics provided by wing with bell shaped lift distribution and generalized wings

Verification of Boundary Conditions Applied to Active Flow Circulation Control

Application of Synthetic Jets Actuators in Wing-Pylon Junction Area to Improve the High Lift Performances

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