A Survey of the Transition Prediction Methods: from Analytical Criteria to PSE and DNS

Arnal, D.; Casalis, Grégoire; Juillen, J. C.

doi:10.1007/978-3-642-79765-1_1

Cited by 14 publications

(10 citation statements)

References 11 publications

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“…This method remains the most widely used method for transition prediction. 6 However, there are some major problems with using this method in practical application. First, the steady laminar solution may be not obtainable in some cases as evidenced by our last test case.…”

Section: Introductionmentioning

confidence: 99%

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Turbulent transition simulation using thek-ω model

Zheng

Liu

et al. 1998

Int. J. Numer. Meth. Engng.

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This paper describes a novel approach in simulating laminar to turbulent transition by using two-equation models. The Total Stresses Limitation (TSL) concept is used to make the two-equation model capable of predicting high-Reynolds-number transitional ow. In order to handle the transition triggered by laminar separation at a low Reynolds number location, which commonly occurs in high speed ow, a sensor is introduced to detect separation and trigger transition in the separated zone. Test cases include the classical at-plate turbulent boundary ow, and low-pressure turbine cascade ows at design and o -design conditions. ? 1998 John Wiley & Sons, Ltd.

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Section: Introductionmentioning

confidence: 99%

“…The envelope method is widely used, but its physical meaning is not clear in many cases. 6 Furthermore, there is no 'universal' value of n factor at the onset of transition, the criteria of determining transition locations varies from case to case.…”

Section: Introductionmentioning

confidence: 99%

Turbulent transition simulation using thek-ω model

Zheng

Liu

et al. 1998

Int. J. Numer. Meth. Engng.

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“…More recent application can be found in the work of Yuan et al [36]. Even though in practice the e N method was extended to study the three-dimensional flow [37], the physical meaning of the envelope method is not clear.…”

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confidence: 99%

Laminar-Turbulent Transition of a Low Reynolds Number Rigid or Flexible Airfoil

2007

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Laminar-turbulent transition can affect the aerodynamic performance of low Reynolds number flyers, such as micro air vehicles that operate at the Reynolds number of 10 4-10 5. To gain better understanding of the fluid physics and the associated aerodynamics characteristics, we coupled a Navier-Stokes solver, the e N transition model, and a Reynolds-averaged two-equation closure to study the low Reynolds number flow characterized with the laminar separation bubble and transition. A new intermittency function suitable for low Reynolds number transitional flow incurred by laminar separation is proposed and tested. With the method, we investigate the performance of a rigid airfoil and a flexible airfoil, mounted with a flexible membrane structure on the upper surface, using SD7003 as the configuration. Good agreement is obtained between the prediction and experimental measurements regarding the transition location, aerodynamic coefficients, and overall flow structures. We also examine the impact of gust on the transition process and airfoil performance. We further investigate the effect of the flexible surface on the transition. We find that the self-excited flexible surface vibration affects the separation and transition positions; however, the time-averaged lift and drag coefficients are close to those of the rigid airfoil. Nomenclature = kinematic eddy viscosity = nondimensionalized time, tc=U ! = specific dissipation rate ! g = gust frequency

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“…All this progress was achieved thanks to the efficient collaboration between Dassault Aviation and Daniel Arnal and his team from ONERA Toulouse. As an example, the linear stability code from ONERA (16-19) computing the amplification N-factor had been used to design the HLFC suction system with six suction flutes (see Fig. 29).…”

Section: Laminarity Controlmentioning

confidence: 99%

An overview of flow control activities at Dassault Aviation over the last 25 years

Rosenblum

2016

Aeronaut.j.

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In France, the very first ideas on flow control were developed by Philippe Poisson-Quinton from the Office National d'Etudes et Recherches Aérospatiales (ONERA) in the 1950s. There was some renewal of this research topic in the early 1990s, first in the United States with scientists like Wygnanski and Gad-El Hak, and also in France at the initiative of Pierre Perrier from Dassault Aviation, who triggered a lot of research activities in this field both at ONERA and in the French National Centre for Scientific Research (CNRS) laboratories. The motivation was driven by the applications on Dassault Aviation military aircraft and Falcon business jets in order to contribute to the design, while facilitating performance optimisation and multi-disciplinary compromise. A few examples of flow control technologies, such as forebody vortex control, circulation control, flow separation control or boundary layer transition control using hybrid laminar flow control (HLFC), are presented to illustrate the applications and to explain the methodology used for the design of the flow control devices. The author also emphasises the current reaction of industry with respect to the integration of flow control technologies on an aircraft programme. The conclusion is related to the present status of the French research on this topic and to the next challenges to be addressed.

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A Survey of the Transition Prediction Methods: from Analytical Criteria to PSE and DNS

Cited by 14 publications

References 11 publications

Turbulent transition simulation using thek-ω model

Turbulent transition simulation using thek-ω model

Laminar-Turbulent Transition of a Low Reynolds Number Rigid or Flexible Airfoil

An overview of flow control activities at Dassault Aviation over the last 25 years

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