Effects of Strake Planform Change on Vortex Flow of a Double-Delta Wing

Sohn, Myung-Hwan; Chung, Hyoung Seog

doi:10.2514/1.30261

Cited by 15 publications

(6 citation statements)

References 14 publications

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“…Previous studies showed intensified interactions between strake and wing vortices as angle of attack increased, due to the increasing sizes and strengths of the vortices. Similar observations were also reported by Gai et al [7] and Sohn and Chung [8]. Two adjacent co-rotating vortices with unequal strengths revolve around a center located on the connecting line between the two vortices.…”

Section: Introductionsupporting

confidence: 88%

Interaction of multiple vortices over a double delta wing

Wang

Gursul

2016

Aerospace Science and Technology

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Interaction of strake and wing vortices over a 70/50 double delta wing were studied experimentally in a wind tunnel using particle image velocimetry (PIV) measurements. The upstream effect of the wing vortex on the formation of the strake vortex was identified. A dual-vortex structure of the strake vortices was observed before the wing vortex developed. Further downstream, wing and strake vortices rotated around each other slowly initially, and then faster with downstream distance, at an increasing rate with increasing incidence. Prior to vortex breakdown, both wing and strake vortices were found meandering in relatively small regions. The correlation between the instantaneous locations of the vortices increases if the vortices become sufficiently close to each other.The proper orthogonal decomposition (POD) analysis of the instantaneous velocity fields suggested that, for both wing and strake vortices, the most energetic mode was displacement in the first helical mode. The most energetic mode reveals out-of-phase displacements when the vortices are close to each other.

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Section: Introductionsupporting

confidence: 88%

Interaction of multiple vortices over a double delta wing

Wang

Gursul

2016

Aerospace Science and Technology

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“…The test parameters are factors influencing the high attack angle aerodynamic characteristics, and the author arbitrarily constructed the forebody design test shape and designated it as a parameter. Three forebody parameters and one strake parameter as listed in Table 2 were selected based on the previous studies on the effects of double delta wing and strake configuration on vortex flow formation and their aerodynamic characteristics (Sohn and Lee, 2004;Sohn and Chung, 2007;Chung et al, 2010;Nelson and Pelletier, 2003).…”

Section: Forebody Design Parametersmentioning

confidence: 99%

Using additive manufactured parametric models for wind tunnel test-based aerodynamic shape optimization

Chung

Kim

Choi

2020

RPJ

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Purpose The purpose of this paper is to propose a new approach of using additively manufactured parametric models in the wind tunnel test-based aerodynamic shape optimization (ASO) framework and to present its applicability test results obtained from a realistic aircraft design problem. Design/methodology/approach For aircraft shape optimization, the following three methodologies were used. First, as a validation study, the possibility of using rapid prototyping (RP) model in the wind tunnel test was verified. Second, through the wind tunnel test-based ASO, the application and feasibility of the real fighter aircraft shape optimization were verified. A generic fighter configuration is parameterized to generate various test models using additive manufacturing. Wind tunnel tests are conducted to measure their stability criteria in high angle of attack (AOA). Finally, a computational fluid dynamics (CFD) study was performed and analysis procedures, costs and results compared to the wind tunnel test were compared and reviewed. Findings RP technology can significantly reduce the time and cost of generating parametric wind tunnel models and can open up new possibilities for wind tunnel tests to be used in the rigorous aerodynamic design loop. There was a slight difference between the results of the RP model and the metallic model because of rigidity and surface roughness. However, the tendency of the aerodynamic characteristics was very similarly predictable. Although there are limitations to obtaining precise aerodynamic data, it is a suitable method to be applied to comparative studies on various shapes with large geo-metric changes in the early phase of design. The CFD analysis indicates that the wind tunnel-based ASO using the RP model shows the efficiency corresponding to the CFD shape optimization. Research limitations/implications The RP parametric models may have various assembly error sources and rigidity problems. The proposed methodology may not be suitable for collecting the accurate aerodynamic database of a final design; rather, the methodology is more suitable to screen out many configurations having fairly large shape variation in the early stage of the design process. Practical implications The wind tunnel test-based ASO can replace or supplement CFD-based ASO. In areas where CFD accuracy is low, such as high AOA flight characteristics, RP model wind tunnel-based ASO can be a research method that can secure both efficiency and accuracy advantages, providing ten times more effective in terms of cost and time. The wind tunnel test is used to obtain aerodynamic data at the final stage of shape design. It can be extended to a comparative study of several shapes in the early design phase. This procedure can be applied for both industrial level and educational aircraft design activities. Originality/value This study is the application to be applied as a parametric study on the whole aircraft, rather than using the RP model applying a simple partial control surface or configuration change of a part of the wing. The possibility of using the RP model was confirmed by comparing and verifying each other in a medium-sized wind tunnel using a relatively large RP model and a metallic model. It was verified that it can be applied in the shape design process, not the shape verification in the traditional design procedure, and a comparison with the CFD method was also performed. With further development and validation efforts, the new design framework may become an industrial standard for future aircraft development.

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“…Malcolm [9] is giving a progress review on forebody vortex control and more recent investigations by Ma and Deng [10] and Zhan and Wang [11] giving an overview about the effect of forebody and leading edge strake as well as the effect of an apex flap on the vortex formation over a delta wing configuration. Additional publications on forebody or chine vortices on delta wing configurations are experimental investigations given by Sohn et al [12,13] who provide the basic flow physics of forebody vortices on a double delta wing. Similar numerical investigation are provided by Jeans at al.…”

Section: Introductionmentioning

confidence: 99%

Impact of Planform and Control Surfaces on the Vortical Flow Topology and Roll Stability of a Multi Delta Wing Configuration

Schuette

2022

AIAA AVIATION 2022 Forum

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Effects of Strake Planform Change on Vortex Flow of a Double-Delta Wing

Cited by 15 publications

References 14 publications

Interaction of multiple vortices over a double delta wing

Interaction of multiple vortices over a double delta wing

Using additive manufactured parametric models for wind tunnel test-based aerodynamic shape optimization

Impact of Planform and Control Surfaces on the Vortical Flow Topology and Roll Stability of a Multi Delta Wing Configuration

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