Parallel Compatible Transition Closure Model for High-Speed Transitional Flow

Xu, Jiakuan; Bai, Junqiang; Fu, Zhenqian; Qiao, Li; Zhang, Yang; Xu, Jinglei

doi:10.2514/1.j055711

Cited by 38 publications

(9 citation statements)

References 36 publications

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“…Sixthly, Xu et al's engineering estimation method [9] for Mach number at the edge of boundary layer is chosen, which has the expressions as follows:…”

Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

“…In recent years, there are two main routes to predict transition for airplanes and other complex aerodynamic configurations. One is the local transition models established by experimental data and stability analysis results, such as Menter et al's γ − Re θt correlation-based transition model [2][3][4], Walters et al's k-k L -ω model based on laminar kinetic energy mechanism [5,6], Fu and Wang's k-ω-γ transition model for high-speed flows [7], and Xu et al's physical mode-based transition models [8][9][10][11]. These models play an important role to predict transition for three-dimensional complex aerodynamic flows.…”

Section: Introductionmentioning

confidence: 99%

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A CFD-Compatible Amplification Factor Transport Equation for Oblique Tollmien-Schlichting Waves in Supersonic Boundary Layers

Qiao

Bai

2020

International Journal of Aerospace Engineering

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Boundary layer transition is a hot research topic in fluid mechanics and aerospace engineering. In low-speed flows, two-dimensional Tollmien-Schlichting (T-S) waves always dominate the flow instability, which has been modeled by Coder and Maughmer from 2013. However, in supersonic flows, three-dimensional oblique Tollmien-Schlichting waves become dominant in flow instability. Inspired by Coder and Maughmer’s NTS amplification factor transport equation for two-dimensional Tollmien-Schlichting waves in low-speed flows and Kroo and Sturdza’s linear stability theory (LST) analysis results for oblique Tollmien-Schlichting waves in supersonic flows, a new amplification factor transport equation for oblique Tollmien-Schlichting waves has been developed based on LST. The compressible Falkner-Skan similarity equations are introduced to build the relationships between nonlocal variables and local variables so that all the variables used in the present model can be calculated using local variables. Applications of this new transport equation to the flows over supersonic flat plate, 3% thick biconvex airfoil, and one modified supersonic laminar airfoil show promising results compared with the standard LST analysis results.

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“…Sixthly, Xu et al's engineering estimation method [9] for Mach number at the edge of boundary layer is chosen, which has the expressions as follows:…”

Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A CFD-Compatible Amplification Factor Transport Equation for Oblique Tollmien-Schlichting Waves in Supersonic Boundary Layers

Qiao

Bai

2020

International Journal of Aerospace Engineering

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“…The transition models that were created to simulate this phenomenon were often designed to accurately represent the transition from laminar to turbulent flow for specific cases, such as bypass transition over a compressor blade [2], natural transition over a flat plate, wake-induced transition over a cascade [3] or hypersonic/supersonic transition through Mack instabilities [4]. Here it is attempted to evaluate the reliability of some of these models for the assessment of the high angle of attack (AoA) behavior of airfoils operating in low Reynolds, external flow conditions.…”

Section: Fig 1 Separation Bubblementioning

confidence: 99%

Comparative Study of Transition Models for High-Angle-of-Attack Behavior

2019

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This paper considers transition modeling for the flow over small unmanned aerial vehicles with a span of around 1 m. Such flows are characterized by very low values of turbulent intensity and the main cause for transition corresponds to flow separation. Four different turbulence models for low Reynolds number flow are compared with the experimental data for a NACA 0018 airfoil over a range of 2D as well as 3D conditions. The turbulence models under consideration are Menter's k − ω SST model with Wilcox's low-Re modification, Menter & Langtry's (k − ω SST) γ − Re θ model along with its simplified version in the form of the (k − ω SST) γ model, and Walters & Coklja's k − k l − ω model. The NACA 0018 profile is rotated in a flow with a chord-based Reynolds number of 3×10 5 at three different rotational speeds between an angle of attack (AoA) of 0 o and 25 o . Using a curve fitting methodology, an estimate of the results at an infinitesimally slow rotation can be made. Both clockwise and counterclockwise rotations are considered to allow an assessment of the model for predicting steady hysteresis. Furthermore, 3D computations for an infinite wing are performed to examine the appearance of coherent structures at high AoA, namely, stall cells or low frequency fluctuations.

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“…The phenomenon of hysteresis can be theoretically described using bifurcation theory 10 by considering the C L (α)-, C D (α)-and C M (α)-characteristics as 10 As critical point theory, bifurcation theory finds its origins in the work of Poincaré, who first introduced the term in 1885. Bifurcation theory studies the branching process of the qualitative, topological picture of an object with a change of the parameters on which the object depends and the stability properties of the bifurcating solutions.…”

Section: Stall Characteristics and Stall Cellsmentioning

confidence: 99%

“…A characteristic of UAVs operating at low Reynolds numbers is the appear- important and this has led to its implementation in commercial software. The turbulence models that were created to simulate this phenomenon were often designed to accurately represent the transition from laminar to turbulent flow for specific cases, such as bypass transition over a compressor blade [6,7], natural transition over a flat plate [8], wake-induced transition over a cascade [9] or hypersonic/supersonic transition through Mack instabilities [10].…”

Section: Introductionmentioning

confidence: 99%

On the study of transitional low-Reynolds number flows over airfoils operating at high angles of attack and their prediction using transitional turbulence models

Wauters

Degroote

2018

Progress in Aerospace Sciences

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In this survey paper transitional turbulence modeling is approached from the point of view relevant to small unmanned aerial vehicles (span ≈ 1m), of which the flow is characterized by very low values of turbulent intensity and transition is predominantly of the separation induced kind. The physical mechanisms that are present during transition are discussed based on the experimental and numerical findings of the last five decades and their influence on high angle of attack behavior, with the appearance of abrupt stall, stall cells, low frequency oscillations and hysteresis are reviewed. Furthermore, an overview will be given of the different methodologies that exist to predict transitional flows. Emphasis will be placed on the modeling of separation bubbles within the RANS-based environment: a number of transitional turbulence models will be summarized and categorized based on their transition predicting methodologies. Four different turbulence models for low Reynolds number flow will be discussed in depth: Menter's k − ω SST model with Wilcox's low-Re modification, Menter & Langtry's (k − ω SST) γ − Re θ model, it's simplified (k − ω SST) γ model and Walters & Cokljat's k − k l − ω model.

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Parallel Compatible Transition Closure Model for High-Speed Transitional Flow

Cited by 38 publications

References 36 publications

A CFD-Compatible Amplification Factor Transport Equation for Oblique Tollmien-Schlichting Waves in Supersonic Boundary Layers

A CFD-Compatible Amplification Factor Transport Equation for Oblique Tollmien-Schlichting Waves in Supersonic Boundary Layers

Comparative Study of Transition Models for High-Angle-of-Attack Behavior

On the study of transitional low-Reynolds number flows over airfoils operating at high angles of attack and their prediction using transitional turbulence models

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