Test
cases
The data for the
estimation of the discretization error/uncertainty of functional and local flow
quantities was obtained from six statistically steady, twodimensional flows of
an incompressible fluid computed with the openusage viscous flow code ReFRESCO
(www.refresco.org):
·
Flow over a flat plate at three
different Reynolds numbers based on the plate length, incoming velocity and fluid kinematic viscosity ,.
I.
.
II.
.
III.
.
·
Flow around a NACA 0012 airfoil at
Reynolds number based on the airfoil chord , incoming velocity and fluid kinematic
viscosity of at three angles of
attack:
IV.
.
V.
.
VI.
.
For these six cases, simulations were
performed with three isotropic eddyviscosity turbulence models:
a.
The
oneequation model of Spalart & Allmaras in the formulation without the
tripping term (SAnoft2).
b.
The
ShearStress Transport (SST) kw twoequation model.
Different cases available will be designated
according to the numbering presented above. For example, CASE IVb corresponds
to the flow around the NACA 0012 airfoil at simulated with the SST kw twoequation model.
All calculations were performed using double
precision (15 digits) and iterative convergence criteria based on the maximum (norm) normalized residual of all transport
equations solved for each flow condition. Normalized residuals are equivalent
to the change of dimensionless dependent variables in a simple Jacobi iteration.
Reference values are the fluid density , and for the plate flow and
, and for the flow around
the airfoils. Maximum values of for the six test cases
are given below.
Test Case 
Flat Plate 
NACA 0012 

I 
II 
III 
IV 
V 
VI 


10^{8} 
10^{8} 
5×10^{8} 
10^{8} 
2×10^{8} 
2×10^{8} 