Efficient Global Optimization of Vortex Generators on a Supercritical Infinite Wing

Namura, Nobuo; Obayashi, Shigeru; Jeong, Shinkyu

doi:10.2514/1.c033753

Cited by 9 publications

(10 citation statements)

References 24 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The optimal values for the configurations on the airfoil are usually found and confirmed by the parametric experiments (Koike et al 2013(Koike et al & 2015, simulations (Ito et al 2016) and multiobjective optimizations using CFD (Kozakai et al 2015, Namura et al 2016. These values are still difficult to predict empirically by using a conceptual model of the VG.…”

Section: Introductionmentioning

confidence: 90%

Wavelet analysis of transonic buffet on a two-dimensional airfoil with vortex generators

Kouchi

Yamaguchi

Koike³

et al. 2016

Exp Fluids

View full text Add to dashboard Cite

We visualized the shock-buffets on a two-dimensional transonic airfoil with and without vortex generators (VGs) by using a fast-framing focusing schlieren imaging. The focusing-schlieren visualization showed that the flow three-dimensionality around the airfoil became remarkable with installing the VGs. This implies that narrow depth of focus of imaging systems was key to accurately capture the characteristics of the shock oscillation due to the buffet for the cases with VGs. The time-resolved imaging also revealed that non-periodic components were included in the shock-oscillation due to the buffet for the cases with VGs. This prevented Fourier analysis from being applied. We used wavelet analysis to extract the characteristic of the shock oscillation for the cases with VGs. The wavelet spectrograms revealed that the low frequency VGs = vortex generators x,y,z = chordwise-, heightwise-, and spanwise-directions, mm

show abstract

Section: Introductionmentioning

confidence: 90%

Wavelet analysis of transonic buffet on a two-dimensional airfoil with vortex generators

Kouchi

Yamaguchi

Koike³

et al. 2016

Exp Fluids

View full text Add to dashboard Cite

show abstract

“…Conventional optimization techniques that optimize a design for a number of operation conditions (multipoint) take a weighted sum of their objective function [24,16]. However, this only moves the problem further downstream: what weight is attributed to which condition?…”

Section: Optimization Frameworkmentioning

confidence: 99%

“…A number of solutions have been developped to tackle the problem of tip stalling, such as vortex generators [24,1] and wing fences [37]. The wing fence, boundary layer fence or potential fence can be defined as a plate which is placed on top of the wing aligned with air flow and, depending on its design, extending up to the trailing edge or extending over the leading edge to the lower surface.…”

Section: Introductionmentioning

confidence: 99%

“…Furthermore, the operation conditions are added as variables that can change continuously. As such, we overcome the limitations of multipoint problems where the objective is optimized in a discrete set of operating conditions [24,16]. In §4 the convergence of the optimization is discussed, as well as the initial design and the Pareto front from an aerodynamic point of view.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Multi-objective optimization of a wing fence on an unmanned aerial vehicle using surrogate-derived gradients

Wauters

Couckuyt

Knudde

et al. 2019

Struct Multidisc Optim

View full text Add to dashboard Cite

In this paper the multi-objective, multi-fidelity optimization of a wing fence on an unmanned aerial vehicle (UAV) near stall is presented. The UAV under consideration is characterized by a blended wing body (BWB), which increases its efficiency, and a tailless design, which leads to a swept wing to ensure longitudinal static stability. The consequence is a possible appearance of a nose-up moment, loss of lift initiating at the tips and reduced controllability during landing, commonly referred to as tip-stall. A possible solution to counter this phenomenon is wing fences: planes placed on top of the wing aligned with the flow and developed from the idea of stopping the transverse component of the boundary layer flow. These are optimized to obtain the design that would fence off the appearance of a pitch-up moment at high angles of attack, without a significant loss of lift and controllability. This brings forth a constrained multi-objective optimization problem. The evaluations are performed through Unsteady Reynolds-Averaged Navier-Stokes (URANS) simulations. However, since controllability cannot be directly assessed through Computational Fluid Dynamics (CFD), surrogate-derived gra-

show abstract

“…Since before that time a number of solutions were introduced to tackle the problem of tip stalling, such as slats, slots, dogtooth, notched leading-edge, leading-edge cuff, leading-edge root extension, vortex generators [5,6], stall strips, pylons, vortilons and wing fences. Based on the solutions presented above, only a handful can be used on the blended wing body aerial vehicle after its manufacturing (typically addressed as aerodynamic afterthoughts).…”

Section: Introductionmentioning

confidence: 99%

Surrogate-Assisted Parametric Study of a Wing Fences for Unmanned Aerial Vehicles

Wauters

Degroote

2021

Journal of Aircraft

View full text Add to dashboard Cite

In this paper the application of a wing fence on an unmanned aerial vehicle (UAV) is examined. The UAV under consideration is characterized by flow separation initiating at the tip, leading to a loss of lift and controllability and the appearance of a nose-up pitching moment. A possible solution to this problem is the use of wing fences: plates placed on top of the wing aligned with the flow and developed from the idea of stopping the transverse component of the boundary layer flow. Firstly, existing theories in regard to the working of wing fences are brought together. Secondly, the sensitivity of stall speed and controllability to the design variables of the wing fence are laid bare. Finally, the aerodynamic and stability characteristics of the UAV as a function of the design variables are assessed. To accomplish the aforementioned three objectives in both an affordable and accurate manner, computational fluid dynamics (CFD) simulations using the − model to correctly model the low Reynolds effects that characterize the flow over a UAV and surrogate modeling in the form of regressive universal co-Kriging are brought together.

show abstract

Efficient Global Optimization of Vortex Generators on a Supercritical Infinite Wing

Cited by 9 publications

References 24 publications

Wavelet analysis of transonic buffet on a two-dimensional airfoil with vortex generators

Wavelet analysis of transonic buffet on a two-dimensional airfoil with vortex generators

Multi-objective optimization of a wing fence on an unmanned aerial vehicle using surrogate-derived gradients

Surrogate-Assisted Parametric Study of a Wing Fences for Unmanned Aerial Vehicles

Contact Info

Product

Resources

About