Numerical Study on Transitional Flows Using a Correlation-Based Transition Model

Halila, Gustavo Luiz Olichevis; Bigarella, E. D. V.; Azevedo, João Luiz F.

doi:10.2514/1.c033311

Cited by 23 publications

(2 citation statements)

References 19 publications

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“…Figure 4. A-airfoil's mesh arrangements: (a) zoomed view; (b) full image.and reattaches near the trailing edge[29]. The turbulent separation region and the shear-layer thickness can be scaled as tiny, which is evidenced by the experiments.…”

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confidence: 74%

An algebraic transition model for fluid flows

Rahman

Hasan

et al. 2023

J. Phys.: Conf. Ser.

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An algebraic (zero-equation) transition model is developed to capture multiple transition mechanisms. The newly devised algebraic transition model is parameterized using “flow-structure-adaptive” variables and coupled with the truncated Spalart-Allmaras (SA) turbulence model. The intermittency factor γ relies on “local flow information” and is directly linked to the “vorticity-based production” term of the SA model. Splitting γ into lower and higher regimes of the “free-stream turbulence intensity” enhances the model coefficient calibration and predictions of various phenomena (“natural, bypass, separation-induced, wake-induced”, etc.) encountered in transitional flows. Simulations approve that the new formulation provides good correspondence with other transition models, available in the literature.

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mentioning

confidence: 74%

An algebraic transition model for fluid flows

Rahman

Hasan

et al. 2023

J. Phys.: Conf. Ser.

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“…The combination of the two parabolic lenses produces an image with illumination rate as function of density gradient. Figure 9 shows in dashed lines 2 light rays which experienced symmetric deflections because Menter 2009; Halila et al 2016). Unfortunately, however, the effort involved in the coding and validation of such an approach would be beyond the available resources here.…”

Section: Schlieren Techniquementioning

confidence: 99%

Visual Experimental and Numerical Investigations Around the VLM-1 Microsatellite Launch Vehicle at Transonic Regime

Mata¹,

Filho²,

Avelar³

et al. 2017

J.Aerosp. Technol. Manag.

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It is performed and presented an experimental and numerical investigation over the flow patterns around the forebody section of a microsatellite launch vehicle in development at Instituto de Aeronáutica e Espaço. The experimental investigation with a VLM-1 model in 1:50 scale is carried out at the Brazilian Pilot Transonic Wind Tunnel, located in the Aerodynamics Division of the mentioned Institute, using the classical schlieren flow visualization technique. Schlieren images are obtained for nominal Mach number varying from 0.9 to 1.01. Numerical simulation using Stanford's SU2 code is conducted together with the experimental investigation in order to improve the understanding of the complex physical phenomena associated with the experimental results of this particular regime. The combination of the 2 techniques allowed the assessment of some important aspects on the flow field around the vehicle in the conditions considered in this study, such as shock wave/boundary-layer interaction. The numerical simulation is also very important, allowing the quantification of some important parameters and confirming the shock wave formation patterns observed in the simulation when compared with the schlieren images. A good agreement regarding the position of the shock wave, when compared with the schlieren images, with a maximum error of about 6%, is observed over the VLM model.

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