Direct numerical simulation of a NACA0012 in full stall

Rodríguez, I.; Lehmkuhl, O.; Borrell, R.; Oliva, A.

doi:10.1016/j.ijheatfluidflow.2013.05.002

Cited by 70 publications

(62 citation statements)

References 34 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…24,25,30 However, to further corroborate the predictive capabilities of the code, we report a new validation of the flow over an aerofoil, where we compare our numerical results with the ones obtained by Lehmkuhl et al 34 and by Rodriguez et al 35 In particular, we have considered a NACA 0012 aerofoil at a chord Reynolds number Re c = 5 × 10 4 at angles of attack α = 5…”

Section: A Validationsupporting

confidence: 53%

See 1 more Smart Citation

Direct numerical simulation of the flow around an aerofoil in ramp-up motion

2016

View full text Add to dashboard Cite

A detailed analysis of the flow around a NACA0020 aerofoil at Rec = 2 × 104 undergoing a ramp up motion has been carried out by means of direct numerical simulations. During the manoeuvre, the angle of attack is linearly varied in time between 0° and 20° with a constant rate of change of α̇rad=0.12U∞/c. When the angle of incidence has reached the final value, the lift experiences a first overshoot and then suddenly decreases towards the static stall asymptotic value. The transient instantaneous flow is dominated by the generation and detachment of the dynamic stall vortex, a large scale structure formed by the merging of smaller scales vortices generated by an instability originating at the trailing edge. New insights on the vorticity dynamics leading to the lift overshoot, lift crisis, and the damped oscillatory cycle that gradually matches the steady condition are discussed using a number of post-processing techniques. These include a detailed analysis of the flow ensemble average statistics and coherent structures identification carried out using the Q-criterion and the finite-time Lyapunov exponent technique. The results are compared with the one obtained in a companion simulation considering a static stall condition at the final angle of incidence α = 20°.

show abstract

Section: A Validationsupporting

confidence: 53%

“…We have used a grid of 2545 × 490 × 48 points in the x 1 , x 2 , and x 3 directions, with a reduced spanwise extent of the domain (set to 0.2c, as in Ref. 35). …”

Section: A Validationmentioning

confidence: 99%

Direct numerical simulation of the flow around an aerofoil in ramp-up motion

2016

View full text Add to dashboard Cite

show abstract

“…The coefficient is normally computed by averaging over combinations of proven that fluctuations in the spanwise direction become uncorrelated when the aspect ratio is sufficiently large [3,23,28,30,51,52].…”

Section: Flow Past An Isolated Airfoil: Simulationmentioning

confidence: 99%

Assessment of spanwise domain size effect on the transitional flow past an airfoil

Zhang

Samtaney

2016

Computers & Fluids

View full text Add to dashboard Cite

Please cite this article as: Wei Zhang, Ravi Samtaney, Assessment of spanwise domain size effect on the transitional flow past an airfoil, Computers and Fluids (2015), doi: 10.1016/j.compfluid.2015 This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting proof before it is published in its final form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain. ACCEPTED MANUSCRIPTA C C E P T E D M A N U S C R I P T Highlights• DNS on the separated-transitional-reattached flow past the airfoil.• The effects of the spanwise domain size are analyzed from various aspects.• The spanwise domain size has significant effects on the various turbulent statistics.• Small spanwise domain size tends to underpredict the spanwise variations.• Examination through only a few quantities may lead to misleading conclusion.

show abstract

“…Therefore, second boundary conditions [3] were adopted in the simulation. (2) In this physical model, the thickness of the tube is 0.…”

Section: Theoretical Modelmentioning

confidence: 99%

Numerical Simulation and Optimization of the Screwed Tube Slot Pitch in New Condenser Tube Slot

Lou¹,

Peng²,

Yao³

2018

dtetr

View full text Add to dashboard Cite

Abstract. In order to improve the heat transfer efficiency of the condenser, a new type of heat exchange tube has been adopted. The heat transfer effect of the new heat exchange tube was further improved because of the screwed pipe. However, due to the complex flow in the condenser, research on this new type of heat exchange tube is mostly in the theoretical stage. In this paper, we present a numerical simulation approach to optimize the slot pitch and verify the results by experiment.

show abstract

Direct numerical simulation of a NACA0012 in full stall

Cited by 70 publications

References 34 publications

Direct numerical simulation of the flow around an aerofoil in ramp-up motion

Direct numerical simulation of the flow around an aerofoil in ramp-up motion

Assessment of spanwise domain size effect on the transitional flow past an airfoil

Numerical Simulation and Optimization of the Screwed Tube Slot Pitch in New Condenser Tube Slot

Contact Info

Product

Resources

About