Active Flow Separation Control Applied at Wing-Pylon Junction of a Wing Section in Landing Configuration

Vrchota, Petr

doi:10.2514/6.2017-0491

Cited by 6 publications

(4 citation statements)

References 9 publications

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“…Prior numerical studies, e.g. [13,21] have noted that these vortices play an important role in the initiation of flow separation when interacting with the attenuated boundary layer flow. In addition, the cove region in between the high-lift elements and the main wing were resolved with structured grid elements according to previous findings [22], see bottom sectional-views in Fig.…”

Section: Computational Gridmentioning

confidence: 99%

Reynolds number and wind tunnel wall effects on the flow field around a generic UHBR engine high-lift configuration

et al. 2020

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RANS simulations of a generic ultra-high bypass ratio engine high-lift configuration were conducted in three different environments. The purpose of this study is to assess small scale tests in an atmospheric closed test section wind tunnel regarding transferability to large scale tests in an open-jet wind tunnel. Special emphasis was placed on the flow field in the separation prone region downstream from the extended slat cut-out. Validation with wind tunnel test data shows an adequate agreement with CFD results. The cross-comparison of the three sets of simulations allowed to identify the effects of the Reynolds number and the wind tunnel walls on the flow field separately. The simulations reveal significant blockage effects and corner flow separation induced by the test section walls. By comparison, the Reynolds number effects are negligible. A decrease of the incidence angle for the small scale model allows to successfully reproduce the flow field of the large scale model despite severe wind tunnel wall effects.

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Section: Computational Gridmentioning

confidence: 99%

Reynolds number and wind tunnel wall effects on the flow field around a generic UHBR engine high-lift configuration

et al. 2020

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“…Conclusions and future directions will be discussed in section 4. In continuation to previous studies on the specific geometry of swept-wing with UHBR nacelle, the current study uses a scaled-down version of the large-scale model (LSM) ( Figure 4) that was windtunnel tested at the closed-loop subsonic wind tunnel T-101 at TsAGI [23][24][25] as part of the AFLoNext project. The current model is scaled down by a factor of 1:8.4, to fit inside the Knapp-Meadow WT with the end-plates of the LSM removed so it spans the entire width of the WT.…”

Section: Figure 2 Cfd Simulation Of the Longitudinal Vortices Formedmentioning

confidence: 99%

Suction and pulsed blowing for control of local wing-engine-slat-cut out flow separation: The INAFLOWT Project

Shay

Posti

Mizrahi

et al. 2020

Aiaa Aviation 2020 Forum

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An experimental study on the application of active flow control (AFC) to a 1:8.4 scale model of a swept wing in a landing configuration was conducted. The wing is fitted with an Ultra High Bypass Ratio (UHBR) engine nacelle. The highly efficient UHBR engines characterized by a large diameter that interferes with the flow around the wing, degrading its performance. An innovative active flow control device, creating steady suction and pulsed blowing (PB), was installed in the leading-edge region of the wing, above the nacelle, and its performance was experimentally evaluated. The effects of the suction and PB mechanisms were examined individually and simultaneously, using relevant normalized parameters to pave the way to a full-scale wind tunnel test. It was shown that the AFC devices increase the lift by up to 3%, redirected the flow to the desired downstream direction and reduced the size of the separation zone created due to the implementation of the UHBR nacelle. The next step is validating the small-scale results of this study in full-scale wind tunnel tests that hopefully make the technology flight test ready.

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“…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. This can be done by modeling the actuator geometry, or at least a significant part like the actuator exit nozzle, to enable development of the velocity profile and to obtain a more realistic flow field at the exit from the actuators [13][14][15][16]. The functional representation for the nozzle oscillatory velocity profiles of the SaOB (Suction and Oscillatory Blowing) actuator was developed in [12], which can be used as surface boundary conditions for complex AFC simulations.…”

Section: Introductionmentioning

confidence: 99%

Verification of Boundary Conditions Applied to Active Flow Circulation Control

2019

Self Cite

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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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Active Flow Separation Control Applied at Wing-Pylon Junction of a Wing Section in Landing Configuration

Cited by 6 publications

References 9 publications

Reynolds number and wind tunnel wall effects on the flow field around a generic UHBR engine high-lift configuration

Reynolds number and wind tunnel wall effects on the flow field around a generic UHBR engine high-lift configuration

Suction and pulsed blowing for control of local wing-engine-slat-cut out flow separation: The INAFLOWT Project

Verification of Boundary Conditions Applied to Active Flow Circulation Control

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