Vortex Flow Control Over a Delta Wing By Co-Rotating and Counter-Rotating Vortex Generator

Chung, Hyoung Seog; Seaver, Christopher A.; McLaughlin, Thomas

doi:10.2514/6.2010-4952

Cited by 2 publications

(4 citation statements)

References 15 publications

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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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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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“…All static data were corrected for the solid tunnel sidewalls and for the wake blockage effects using the methods offered by Barlow et al 19 An analytical approach was also exploited to estimate the errors involved in the pressure measurements. 20 The minimum inherent error of a 64-channel A/D board is AE10/2 12 V and for a 16-channel board, this value would be AE10/2 16 V. Both boards were used in the present experiments depending on the pressure range of the transducers. Once the necessary corrections were applied to the results, the total errors encountered by the measured data including the accuracy of the electronic devices such as transducers and the acquisition boards were calculated to be less than AE3%.…”

Section: Experimental Setup and Proceduresmentioning

confidence: 99%

“…12 Having extended the existing knowledge on wing-canard interactions, the idea of using split canards was found to be an alternative way to enhance the aerodynamic performance of vehicles equipped with this type of control surface and operating at high angles of attack. Some of the modern highly maneuverable vehicles today use split canards for their flight control.…”

Section: Introductionmentioning

confidence: 99%

“…In recent years, the studies on the aerodynamics of canard-wing-body configurations, has mainly been focused on vortical flow control over these bodies including flow control by spanwise pulsed blowing 10,11 and through developing active flow control actuator for delta wing in strake-delta wing configurations. 12 Having extended the existing knowledge on wing-canard interactions, the idea of using split canards was found to be an alternative way to enhance the aerodynamic performance of vehicles equipped with this type of control surface and operating at high angles of attack. Some of the modern highly maneuverable vehicles today use split canards for their flight control.…”

Section: Introductionmentioning

confidence: 99%

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Canard flow improvement in a split canard configuration

Davari

Askari

Soltani

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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Extensive low-speed wind-tunnel tests are performed to study the flow field structure over a dual-surface canard, known as split canard, in comparison to the conventional configurations. Surface pressure for both steady deflections and unsteady oscillations of the canard are measured and compared for both canard-alone and split-canard cases. The split canard shows a superior advantage at high angles of attack, where a delay in the vortex breakdown phenomena on the canard surface is observed. For the split-canard configuration, the downwash of the front canard reduces the effective angle of attack at the inboard section of the rear element which postpones formation of the leading-edge vortex. Furthermore, a region of considerably high suction was observed at front portion of the rear canard when compared with the isolated canard case. This can be thought of as the main mechanism of performance enhancement in split canards comparing to the conventional configurations.

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Vortex Flow Control Over a Delta Wing By Co-Rotating and Counter-Rotating Vortex Generator

Cited by 2 publications

References 15 publications

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

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

Canard flow improvement in a split canard configuration

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