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Simulation of Turbulent Flow around an Airfoil
57:020 Mechanics of Fluids and Transfer Processes
CFD PRELAB 2
By Tao Xing and Fred Stern
IIHRHydroscience & Engineering
The University of Iowa
C. Maxwell Stanley Hydraulics Laboratory
Iowa City, IA 522421585
1. Purpose
The Purpose of CFD PreLab 2 is to simulate
turbulent
flow around Clarky airfoil following “CFD process”
by an interactive stepby
step approach. Students will have “hands

on” experiences using FlowLab to
compute pressure, lift and drag coefficients using both
viscous and inviscid
models. Students will
validate
simulation results with EFD data measured at EFD Lab 3, analyze the differences and possible numerical
errors, and present results in Lab report.
2. Simulation Design
In EFD Lab 3, you have conducted experimental study for turbulent flow around a ClarkY airfoil
(Re=300,000) for two angles of attack 0 and 16 degrees. The pressure on the foil surface you have measured
Flow chart for ISTUE teaching module for airfoil flow (red color illustrates the
options you will use in this CFD PreLab 2)
Geometry
Postprocessing
Report
Physics
Mesh
Contours
Vectors
Streamlines
Solve
Iterations
Conver
gent.
Limit
Precisions
Single
Double
Numerical
Schemes
1
st
order
2
nd
order
QUICK
Steady
/
Unsteady?
Coarse
Medium
Fine
Automatic
Manual
Structured
Unstruct
ured
Boundary
Conditions
Flow
Properties
Viscous
Models
One Eq.
Two Eq.
Density and viscosity
Laminar
Turbulen
Inviscid
SA
ke
kw
Heat
Transfer?
Incompress
ible?
Initial
Conditions
Clarky
NACA12
LS(1) 0417
Import Profile
Chord length
Angle of attack
Select domain
Select geometry
Wall shear
stress
Skin friction
Factor
XY plots
Verification
and validation
Coefficient of
lift
Coefficient of
drag
Residuals
Pressure coef. Distri.
Shear stress Distri.
Airfoil Y plus
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will be used for CFD PreLab 2. In CFD PreLab 2, simulation will be conducted under the same conditions of
EFD Lab 3 (geometry, Reynolds number, fluid properties) at angle of attack 0 degree using both viscous and
inviscid models. Simulation results will be validated by your own EFD data.
The problem to be solved is turbulent flow around the ClarkY airfoil with angle of attack (
)
In the figure above, C is the chord length of the airfoil,
is the angle of attack, and Rc is the radius of the
“O” domain
.
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This note was uploaded on 12/08/2011 for the course MECHANICS 57:020 taught by Professor Fredrickstern during the Fall '10 term at University of Iowa.
 Fall '10
 FredrickStern
 mechanics

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