Prediction of the flow over a circular cylinder at high Reynolds number using detached-eddy simulation

Squires, Kyle D.; Krishnan, V.S.; Forsythe, James R.

doi:10.1016/j.jweia.2008.02.053

Cited by 34 publications

(20 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The current state of these approaches will be shown in the invited lectures at this conference by Profs. Hanjalic and Squires [94,95]. 23 36 37 58 59 60 62 70 71 72 22 34 35 46 47 48 49 50 51 52 53 54 55 65 66 67 68 69 74 77 78 79 2 3 4 5 14 15 16 24 25 26 27 28 29 30 38 41 42 43 44 56 57 61 63 64 73 1 6 7 8 9 10 11 12 13 17 18 19 20 21 31 32 33 39 40 45 75 76 16 24 25 26 27 28 29 30 37 38 41 56 57 58 59 60 61 62 63 64 70 71 72 73 39 40 50 51 52 53 54 55 75 76 2 3 4 5 14 15 23 36 42 43 44 1 6 7 8 9 10 11 12 13 17 18 19 20 21 22 31 32 33 34 35 45 46 47 48 49 65 66 67 68 69 74 77 78 79 23 36 37 58 59 60 62 70 71 72 22 34 35 46 47 48 49 50 51 52 53 54 55 65 66 67 68 69 74 77 78 79 2 3 4 5 14 15 16 24 25 26 27 28 29 30 38 41 42 43 44 56 57 61 63 64 73 1 6 7 8 9 10 11 12 13 17 18 19 20 21 31 32 33 39 40 45 75 76 16 24 25 26 27 28 29 30 37 38 41 56 57 58 59 60 61 62 63 64 70 71 72 73 39 40 50 51 52 53 54 55 75 76 2 3 4 5 14 15 23 36 42 43 44 1 6 7 8 9 10 11 12 13 17 18 19 20 21 22 31 32 33 34 35 45 46 47 48 49 65 66 67 68 69 74 77 78 79 80 normalized scalar velocity Exp.…”

Section: Aij Collaborative Research Project -Cross Comparisons Of Cfdmentioning

confidence: 99%

Prediction of wind environment and thermal comfort at pedestrian level in urban area

Mochida

Lun

2008

Journal of Wind Engineering and Industrial Aerodynamics

285

116

View full text Add to dashboard Cite

Section: Aij Collaborative Research Project -Cross Comparisons Of Cfdmentioning

confidence: 99%

Prediction of wind environment and thermal comfort at pedestrian level in urban area

Mochida

Lun

2008

Journal of Wind Engineering and Industrial Aerodynamics

285

116

View full text Add to dashboard Cite

“…Since its first introduced by Spalart and his co-workers in 1997 [15] , this methodology has been successfully applied to wider engineering flow problems, including circular cylinder, airfoils, aircraft fore-bodies, fighter aircraft and others cases, e.g. Wang et al [16] , Chen et al [17] , Tarvin et al [18] , Spalart [19] , and Viswanathan et al [20][21][22] For the blade trailing-edge cooling study in particular, DES with the Spalart-Allmaras model has been applied by Martini et al [6] with improved predictions over that of the RANS method.…”

Section: Methodology and Definitionmentioning

confidence: 99%

Predicting Film Cooling Performance of Trailing-Edge Cutback Turbine Blades by Detached-eddy Simulation

Effendy¹,

Yao

et al. 2014

52nd Aerospace Sciences Meeting

View full text Add to dashboard Cite

This paper describes numerical studies of the film cooling performance of cutback trailing-edge gas turbine blades using the detached eddy simulation (DES) approach, in order to improve results obtained by industry standard steady RANS and unsteady RANS (URANS). An experimental configuration of blade cooling slot with two rows of long ribs at three different blowing ratios (M = 0.5, 0.8, 1.1) are investigated and three aforementioned numerical approaches based on the same SST k-ω turbulence model are adopted. Simulation flow conditions follow experimental and numerical studies previously done by other researchers. At a low blowing ratio M = 0.5, current numerical predictions have shown that DES results are in good agreement with available experimental measurement of film cooling effectiveness along the trailing-edge cutback surface, whereas both RANS and URANS largely over-predict in the near and far wake regions. At a moderate blowing ratio M = 0.8, DES slightly over-predicts the film cooling effectiveness after a nondimensional streamwise location x/H > 8 (with H denotes the slot height), whereas at a high blowing ratio M = 1.1 it under-predicts after x/H > 5. The effect of lip thickness has also been studied and it was found that a thinner lip thickness t/H = 0.5 (with t denotes the lip thickness) produces an adiabatic film cooling effectiveness of near unity along the trailing-edge cutback surface, indicating that there is need to reduce the lip thickness to achieve a higher level of cooling effectiveness, without compromising other constraints such as blade structure and loadings. NomenclatureA slot = area of slot exit [m 2 ] b r = thickness of internal coolant passage ribs [mm] des C = calibration constant used in DES model (C des = 0.61) D ω = cross-diffusion term f = frequency [kHz] F DES = blending function in DES model 2 G k = generation of turbulence kinetic energy due to the mean velocity gradients G ω = generation of turbulence dissipation rate ω H = height of internal coolant passage slot [mm] k = turbulent kinetic energy k = laterally averaged turbulent kinetic energy L 0,1,2.3 = streamwise lengths of main hot gas domain [mm] L r1,r2 = lengths of row 1 and row 2 ribs [mm] t L = turbulence length scale M ∞ = Mach number M = blowing ratio c m  = mass flow rate of coolant gas [kg/s] q conv = convective heat flux [W/m 2 ] q rad = radiative heat flux [W/m 2 ] q w = wall heat flux [W/m 2 ] R f = fillet radius [mm] s = pitch-wise distance of ribs array [mm] S t = Strouhal number S 1 = the first monitoring point location S 2 = the second monitoring point location S k = source terms in turbulence kinetic equation S ω = source terms in turbulence dissipation equation t = thickness of blade trailing-edge [mm] T aw = adiabatic wall temperature [K] aw T = laterally averaged adiabatic wall temperature [K] T w = isothermal wall temperature [K] T c = coolant gas temperature [K] T hg = hot gas temperature [K] u c = coolant gas velocity [m/s] u hg = hot gas velocity [m/s] X r1,r2 = x-coordinates of row 1 and row 2 ...

show abstract

“…The purpose of this study is to show the approach to determining sheathing roughness of flow over a circular cylinder at high Re numbers by numerical modeling using the finite volume method in AN-SYS Fluent software. This is a complex problem of flow in the critical area, the solution of which is dealt with by many international departments, whether in experimental [1], [2], [3], [4] or numerical [5], [6], [7], [8], [9], [10], [11], [12], [13] research.…”

Section: Introductionmentioning

confidence: 99%

Flow over Rough–Walled Circular Cylinder in the Critical Area

Lausová¹,

Kološ²,

Michalcová³

2019

TCES

View full text Add to dashboard Cite

The article deals with the flow over a roughwalled circular cylinder in the critical area at high Re numbers. The subject of the paper is a comparison of the standard calculation of the aerodynamic drag coefficient with numerical modeling. Numerical tasks are solved by the simplified geometry of the smooth cylinder, where the influence of the rough surface is given by the equivalent aerodynamic roughness, and also by the model with the real geometry of the rough casing of the cylinder.

show abstract

Prediction of the flow over a circular cylinder at high Reynolds number using detached-eddy simulation

Cited by 34 publications

References 8 publications

Prediction of wind environment and thermal comfort at pedestrian level in urban area

Prediction of wind environment and thermal comfort at pedestrian level in urban area

Predicting Film Cooling Performance of Trailing-Edge Cutback Turbine Blades by Detached-eddy Simulation

Flow over Rough–Walled Circular Cylinder in the Critical Area

Contact Info

Product

Resources

About