Numerical study of turbulent trailing-edge flows with base cavity effects using URANS

Do, Thau; Chen, Li; Tu, Jiyuan

doi:10.1016/j.jfluidstructs.2010.07.006

Cited by 27 publications

(11 citation statements)

References 34 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The results show an asymmetric wake behind the smaller beveled trailing edge contrary to the greater one that a symmetric wake is observed. The flow past a hydrofoil with blunt and various base cavity shapes at high Reynolds numbers was studied numerically (Do et al, 2010). The base cavity at the trailing edge has effect on the wake structure, decreasing the intensity of the trailing edge pressure fluctuations.…”

Section: Introductionmentioning

confidence: 99%

How oblique trailing edge of a hydrofoil reduces the vortex-induced vibration

Zobeiri

Ausoni

Avellan

et al. 2012

Journal of Fluids and Structures

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

How oblique trailing edge of a hydrofoil reduces the vortex-induced vibration

Zobeiri

Ausoni

Avellan

et al. 2012

Journal of Fluids and Structures

View full text Add to dashboard Cite

“…In terms of the absolute level, the current model provides the best comparison to the experimental data. It should be noted that the peak at 3 kHz in the experimental data is associated with vortex shedding from the trailing edge, which has been successfully captured by our unsteady RANS simulation [42]. It should be straightforward to combine the results of the current and unsteady simulations, but that is beyond the scope of this paper.…”

Section: Predicted Surface Pressure Spectrummentioning

confidence: 94%

“…The simulations were carried out with four different meshes to ensure grid independence. To avoid repetition, the details of the CFD simulation, including mesh independence studies and model validations, can be found in our previous work [42].…”

Section: B Flow Simulationmentioning

confidence: 99%

Prediction of Trailing-Edge Noise Based on Reynolds-Averaged Navier–Stokes Solution

Chen

MacGillivray

2014

AIAA Journal

Self Cite

View full text Add to dashboard Cite

Trailing-edge noise is a significant component of the noise generated by low-Mach-number wall-bounded turbulent flow. It is therefore important to develop an efficient method for computing this noise in practical applications. Instead of using computationally expensive methods or an empirical model to predict the true time history of surface pressure, a model of trailing-edge noise for a hydrofoil combining widely used computational-fluid-dynamics Reynoldsaveraged Navier-Stokes solutions with the edge source acoustic Green's function of arbitrary chord is presented. The model takes the nature of the anisotropic turbulence in boundary-layer flow derived from Reynolds-averaged Navier-Stokes solution into consideration. The model has been applied to the trailing-edge noise of a NACA 0012 foil at a chord-based Reynolds number equal to 2.36 × 10 6 and to a strut with hemicylindrical leading edge and tapered trailing edge at Reynolds number equal to 5.12 × 10 5 . It has been compared with existing empirical models, and a significant improvement has been obtained. The predicted results are in good agreement with existing experimental data. Nomenclaturein the model spectrum density c 0 = speed of sound in the far field, m∕s E 0 ψ , E N ψ = normalized model cross-spectrum density of velocity E N 22 = normalized cross-spectrum density of u 0 2 G = Green's function K = κ 2 1 κ 2 3 p , 1∕m K ν = νth-order Bessel function k = turbulence kinetic energy, m 2 ∕s 2 L s = spanwise length of foil, m l i = pressure fluctuation correlate length scale in i direction, m p = hydrodynamic pressure, Pa p = mean pressure, Pa p 0 = pressure fluctuation, Pa p a = acoustic pressure, Pa p aI = incident acoustic pressure, Pa U c = convection velocity in streamwise direction, m∕s u = velocity vector, m∕s u i = mean velocity in i direction, m∕s u 0 i = velocity fluctuation in i direction, m∕s u = wall shear velocity, m∕s x, x 0 = coordinate vector, with i equal to 1 (streamwise), 2 (vertical), or 3 (spanwise), m y y i = observation coordinates, m δ = boundary-layer thickness, m δ = boundary-layer displacement thickness, m κ i = wave number in i direction, 1∕m κ 0 = acoustic wave number, 1∕m Λ = streamwise turbulence integral length scale, m μ = dynamic viscosity of fluid, kg∕m · s ρ = density of fluid kg∕m 3= radiated trailing-edge noise spectrum for a semiinfinite foil, Pa 2 ∕Hz ϕ pp = point surface pressure spectrum, Pa 2 ∕Hz ψ = angle between the observer direction and the trailing edge of a foil, deg ω = angular frequency, rad∕s

show abstract

“…Kim et al (2004) and Park et al (2006) employed active and passive control methods to find an efficient way to control trailing edge vortex shedding of half-ellipse shaped bodies. Do et al (2010), Liu et al (2007), and Tang and Dowell (2006)control the aerodynamic flow of an airfoil with different modifications of the trailing edge. It is indicated that the thin extended trailing edge can enhance the lift, whereas the zero-lift drag is not significantly increased.…”

mentioning

confidence: 99%