On the performance of RANS turbulence models in predicting static stall over airfoils at high Reynolds numbers

Nived, M. R.; Mukesh, Bandi Sai; Athkuri, Sai Saketha Chandra; Eswaran, V.

doi:10.1108/hff-08-2021-0519

Cited by 10 publications

(3 citation statements)

References 41 publications

(62 reference statements)

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“…With the classic k - ∈ turbulence model and Reynolds stress model (RSM), a medium Re (360,000) case has been assessed by Almohammadi (2022) for up to 20° AoA. For high Re , Nived et al (2022) investigated fluid flow with Spalart–Allmaras (SA) model, Menter’s k - ω SST model, k - kL model and SA-Bas Çakmakçıoğlu modified (SA-BCM) transition model (Çakmakçıoğlu et al , 2020).…”

Section: Resultsmentioning

confidence: 99%

Experimental and LBM analysis of medium-Reynolds number fluid flow around NACA0012 airfoil

Rak

Grbčić

Sikirica

et al. 2023

HFF

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Purpose The purpose of this paper is the examination of fluid flow around NACA0012 airfoil, with the aim of the numerical validation between the experimental results in the wind tunnel and the Lattice Boltzmann method (LBM) analysis, for the medium Reynolds number (Re = 191,000). The LBM–large Eddy simulation (LES) method described in this paper opens up opportunities for faster computational fluid dynamics (CFD) analysis, because of the LBM scalability on high performance computing architectures, more specifically general purpose graphics processing units (GPGPUs), pertaining at the same time the high resolution LES approach. Design/methodology/approach Process starts with data collection in open-circuit wind tunnel experiment. Furthermore, the pressure coefficient, as a comparative variable, has been used with varying angle of attack (2°, 4°, 6° and 8°) for both experiment and LBM analysis. To numerically reproduce the experimental results, the LBM coupled with the LES turbulence model, the generalized wall function (GWF) and the cumulant collision operator with D3Q27 velocity set has been used. Also, a mesh independence study has been provided to ensure result congruence. Findings The proposed LBM methodology is capable of highly accurate predictions when compared with experimental data. Besides, the special significance of this work is the possibility of experimental and CFD comparison for the same domain dimensions. Originality/value Considering the quality of results, root-mean-square error (RMSE) shows good correlations both for airfoil’s upper and lower surface. More precisely, maximal RMSE for the upper surface is 0.105, whereas 0.089 for the lower surface, regarding all angles of attack.

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Section: Resultsmentioning

confidence: 99%

Experimental and LBM analysis of medium-Reynolds number fluid flow around NACA0012 airfoil

Rak

Grbčić

Sikirica

et al. 2023

HFF

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“…Turbulent separation bubble starting from leading edge is predicted by 𝑘𝑘 − 𝜔𝜔 SST turbulence model at this angle of attack. From Figure 5 it can be observed that the flow stalls at 9-degree angle of attack and the performance of RANS based turbulence models in the pre and post stall regions are not reliable (25,26). Thus, the special flow separation behavior observed at these angles of attack need to be validated with experiments or LES/DNS simulations.…”

Section: Validation Of Transition 𝑘𝑘 − 𝜔𝜔 Sst Turbulence Modelmentioning

confidence: 99%

Steady and Time Dependent Study of Laminar Separation Bubble (LSB) behavior along UAV Airfoil RG-15

2023

IJM

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The flow around the Unmanned Arial Vehicle (UAV) operating at a low Reynolds number regime of the O(10 5 ) is predominantly laminar and it leads to the formation of Laminar Separation Bubble (LSB). The pressure, shear stress, and heat flux distribution are considerably affected by LSB, which affects lift, drag, and pitching moment values. Most existing RANS (Reynolds-Averaged Navier-Stokes) turbulence models are built on the assumption of fully turbulent flow. Therefore, these models require additional transport equations or reformulations or specific transition information to predict the LSB observed in low Reynolds number transition flows. Steady and transient computational fluid dynamics simulations were done using the RANS based transition turbulence model to study the behavior of LSB on UAV airfoil RG-15. The transition turbulence model can predict the LSB with considerable accuracy. The steady state and time averaged simulation results are matching in the pre stall region but deviates after stalling. High amplitude velocity fluctuations were observed near regions of transition and separation.

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“…In another investigation, they analyzed the influence of this flow control on NACA 0025 at different Reynolds numbers (Khoshnevis et al, 2020). Some interesting results on this topic can be found in Gleize et al (2022), Nived et al (2022).…”

Section: Introductionmentioning

confidence: 99%

Effects of coflow-jet active flow control on airfoil stall

Yazdani

Salimipour²,

Salimipour³

et al. 2023

HFF

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Purpose Active flow control on the NACA 0024 airfoil defined as suction-injection jet at the chord-based Reynolds number of 1.5 × 1e + 5 is studied. Design/methodology/approach The three-dimensional incompressible unsteady Reynolds-averaged Navier–Stokes equations with the SST k-ω turbulence model are used to study the effects of coflow-jet (CFJ) on the dynamic and static stall phenomena. CFJ implementation is conducted with several momentum coefficients to investigate their turnover. Furthermore, the current work intends to analyze the CFJ performance by varying the Reynolds number and jet momentum coefficient and comparing all states to the baseline airfoil, which has not been studied in prior research investigations. Findings It is observed that at the momentum coefficient (Cµ) of 0.06, the lift coefficients at low attack angles (up to a = 15) dramatically increase. Furthermore, the dynamic stall at the given Reynolds number and with the lowered frequency of 0.15 is explored. In the instance of Cµ = 0.07, the lift coefficient curve does not show a noticeable stall feature compared to Cµ = 0.05, suggesting that a more powerful stronger jet can entirely control the dynamic stall. Originality/value Furthermore, the current work intends to analyze the CFJ performance by varying the jet momentum coefficient and comparing all states to the baseline airfoil, which has not been studied in prior research investigations.

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On the performance of RANS turbulence models in predicting static stall over airfoils at high Reynolds numbers

Cited by 10 publications

References 41 publications

Experimental and LBM analysis of medium-Reynolds number fluid flow around NACA0012 airfoil

Experimental and LBM analysis of medium-Reynolds number fluid flow around NACA0012 airfoil

Steady and Time Dependent Study of Laminar Separation Bubble (LSB) behavior along UAV Airfoil RG-15

Effects of coflow-jet active flow control on airfoil stall

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