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Workshop 2
Transonic Flow Over aNACA 0012 Airfoil.
Introduction to CF
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Workshop Supplement !oals
%he p&rpose o' this t&torial is to introd&ce the &ser to #odelling 'lo( in
high speed e)ternal aerodyna#ic applications.
In this case the 'lo( over a NA*A 0012 air'oil at an angle o' attach o' 1.+
(ill $e si#&lated and the li't and drag val&es (ill $e co#pared to p&$lished
res<s. %hese res<s (ere taen (ith a eynolds n&#$er o' )10/ and a
chord length o' 1#.
%he air'oil is travelling at ach 0. so the si#&lation (ill need to acco&nt
'or co#pressi$ility as (ell as t&r$&lence e''ects.
%o red&ce the co#p&tational cost, the #esh (ill $e #ade &p o' a 2" slice
thro&gh the air'oil 3one ele#ent thic4.
NASA % 512 %(o-"i#ensional Aerodyna#ic *haracteristics o' the NA*A 0012 Air'oil in the 6angley 5-7oot %ransonic Press&re %&nnel 151.
8arris, *. ".
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Workshop Supplement "tart a Work#ench pro$ect
1. 6a&nch Wor$ench
2. Save the ne( pro9ect as naca0012 in yo&r(oring directory
!. "rag a Fluid Flow (CFX) #od&le 'ro# the
Analysis Systems section o' the Toolo!
onto the "ro#ect Schematic
+. In the "ro#ect Schematic right-clic on the$esh cell and select %mport $esh File
:. Set the 'ile 'ilter to F&'T Files and select
ACA0012*msh
– With the #esh 'ile i#ported the +eometry cell
(ill not $e needed so it is re#oved 'ro# theFluid Flow #od&le.
Note that yo& co&ld have dragged Component System , CFX onto the Pro9ect
Sche#atic, as in the 'irst (orshop. %he #esh (o&ld then $e i#ported a'ter
starting *7;-Pre.
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Workshop Supplement %esh %odification
1. <pen *7;-pre $y right-clicing on the Setup cell and
selecting dit
– A'ter *7;-Pre has opened the #esh can $e e)a#ined
and it is clear that the scale is incorrect as the air'oil
chord is 1000 # rather than 1 #, indicating the #esh
(as $&ilt in ## rather than #. %his can $e 'i)ed &sing
the #esh trans'or#ation options.
2. ight-clic on $esh in the -utline tree and selectTrans.orm $esh
!. *hange the Trans.ormation to Scale
+. 6eave the #ethod to 'ni.orm and enter a 'ni.orm
Scale o' 0*001
:. *lic -/
/. Select the Fit iew icon 'ro#
the =ie(er tool$ar
– >oo# in '&rther to see the air'oil
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Workshop Supplement %esh %odification
%he #esh has $een $&ilt to have a single
$o&ndary aro&nd the entire o&ter edge. %his
needs to $e split into inlet and o&tlet regions.While it is $etter to create the correct #esh
regions (hen generating the #esh, *7;-Pre
can $e &sed to #odi'y the #esh regions.
1. ight-clic $esh in the -utline tree and select%nsert , "rimitie e3ion
2. *lic on the Start "ickin3 $&tton
!. 7ro# the drop do(n selection #en& select
Flood Select 3see i#age to the right4
+. In the vie(er select any ele#ent 'ro# the 'rontc&rved $o&ndary
– %he 'lood 'ill (ill select all cells (here the change
in angle is less than !0
:. *lic in the $oe Faces To 'ield and type %nlet
/. *lic -/
Inlet
Outlet
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Workshop Supplement %esh %odification
%he re#aining section (ill no( $e
rena#ed ?<&tlet@.
1. )pand the $esh section o' the tree so
the list o' "rincipal 24 e3ions is
visi$le. Note that this list no( contains
the location %nlet 2. *lic on the region pressure .ar .ield 1
to con'ir# it is the region representing
the o&tlet
– It (ill $e highlighted in the =ie(er
!. ight-clic on pressure .ar .ield 1 andselect ename. *hange the na#e to
-utlet
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Workshop Supplement &o'ain "etup
Bs&ally the option to a&to#atically generate do#ains is active, this can
$e checed $y editing Case -ptions , +eneral in the <&tline tree.
1. *hec that Automatic 4e.ault 4omain is active the clic <C.
2. ight-clic on 4e.ault 4omain in the <&tline tree and rena#e it to Fluid
!. "o&$le-clic on Fluid to edit the do#ain settings
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Workshop Supplement &o'ain "etup
%his case involves high speed aerodyna#ics so it is i#portant to incl&de
co#pressi$ility.
It is i#portant to set the correct operating press&re so that the intended eynolds
n&#$er is achieved. %he si#&lation (ill tae place at 255 DCE in airF this allo(s the
speed o' so&nd to $e calc&lated. %his can then $e converted into a 'ree-strea#
velocity &sing the ach n&#$er. Bsing the de'inition 'or eynolds n&#$er the 'l&id
density can $e o$tained, (hich can then $e &sed to deter#ine the operatingpress&re 'or the si#&lation, ass&#ing an ideal gas.
][56867288287688.0
]/[688.0112.238
82.19ReRe
]/[12.23817.3407.0
]/[17.3402882874.1
356
Pa RT P
mkg ee
ul
ul
smc M u
sm RT c
=××==
=
×
×==⇒=
=×=×=
=××==
−
ρ
µ ρ
µ
ρ
γ c GSpeed o' so&nd
GHas *onstant
5 Gatio o' speci'ic heatsT G%e#perat&re
uG 7ree-strea# velocity
$ Gach n&#$er
eGeynolds n&#$er
6 G "yna#ic viscosity
7G "ensity
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Workshop Supplement &o'ain "etup
In the Fluid do#ain 8asic Settin3s ta$
1. Set the aterial to Air %deal +as
2. Set the e.erence "ressure to 9:;:< ="a>
– ae s&re yo& change set the &nits
!. ove to the Fluid $odels ta$
+. Set the ?eat Trans.er -ption to Total ner3y
– %his is reJ&ired 'or co#pressi$le si#&lations
:. na$le %ncl* iscous Work Term
– %his incl&des visco&s heating e''ects
/. Set the Turulence -ption to Shear StressTransport
. *lic -/
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Workshop Supplement (oundar) Conditions
An o&tlet relative press&re o' 0 DPaE (ill no( $e applied. %his press&re is relative
to the operating press&re o' :/5/ DPaE.
Asolute "ressure @ e.erence "ressure elatie "ressure
1. ight-clic on the do#ain Fluid in the <&tline tree and select %nsert , 8oundaryB
na#ing the $o&ndary -utlet
2. *hange the 8oundary Type to -utlet and chec that the location is set to -utlet
!. ove to the 8oundary 4etails ta$ and set the $ass and $omentum option to
Aera3e Static "ressure (ith a val&e o' 0 ="a>
+. *lic -/
%he sides o' the do#ain (ill &se sy##etry conditions since this is a 2"
si#&lation.
1. Insert a Symmetry $o&ndary called Sym &e.t , at the location sym le.t
2. Insert a Symmetry $o&ndary called Sym i3ht , at the location sym ri3ht
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Workshop Supplement (oundar) Conditions
%he #esh has $een constr&cted so that the air'oil is at 0 angle o'
attac. %o apply the reJ&ired angle o' 1.+ the 'lo( direction at the inlet
#&st $e ad9&sted. %he val&es (ill $e created &sing e)pressions.
1. ight-clic on !pression in the tree and select %nsert , !pression. *all
it 'in. .
2. Set the 4e.inition to 2;*12 =m sDE1> then clic Apply – All e)pressions #&st have the appropriate di#ensions
!. In the e)pression editor add the 'ollo(ing e)pressions $y right-clicing
on !pressions and selecting %nsert , !pression
A-A @ 1*G=de3>
'! @ 'in.Hcos(A-A)
'y @ 'in.Hsin(A-A)
+. et&rn to the #ain <&tline tree
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Workshop Supplement (oundar) Conditions
1. ight-clic on Fluid and insert a $o&ndary
called %nlet
2. %he 8oundary Type sho&ld $e set to %nlet $y
de'a< and a &ocation o' %nlet sho&ld also
$e selected $y de'a<
!. ove to the 8oundary 4etails ta$
+. *hange the $ass and $omentum option toCart* el* Components
:. nter the B, = and W val&es as '!B 'y and
0 =m sDE1>
– Bse the )pression icon to allo( the '!
and 'y e)pressions to $e entered/. Set Static Temperature G 2;; =/>
. *lic -/
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Workshop Supplement (oundar) Conditions
%he =ie(er indicates the locations o'
the inlet and o&tlet $o&ndaries. Note
that the arro(s do not represent the
applied 'lo( direction.
%he 'inal $o&ndary condition is the (all
aro&nd the air'oil. %his sho&ld alreadye)ist as Fluid 4e.ault .
1.dit Fluid 4e.ault to chec that only the
wall ottom and wall top regions re#ain
in the de'a< $o&ndary2.*lic Close
!.ena#e Fluid 4e.ault to Air.oil
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Workshop Supplement %onitors
7or this si#&lation the li't and drag are the J&antities o' interest, so #onitor points
(ill $e added to trac their val&es and ens&re they reach a steady val&e. %he li't
and drag coe''icients (ill $e created &sing e)pressions. e#e#$er that the 'ree-
strea# 'lo( is o''set 'ro# the )-direction so the 'orces (ill have to $e ad9&sted to
acco&nt 'or the angle o' attac.
1.nter the 'ollo(ing e)pressions, or select
File , %mport , CC& and load the 'ile Air.oil*ccl . I' loading the **6 'ile, &se
the Append option as sho(n
[email protected]()JAir.oil
[email protected]!()JAir.oil
&i.t @cos(A-A)HFyEsin(A-A)HF!
4ra3 @cos(A-A)HF! sin(A-A)HFy
4enom@0*9HmassFlowAe(4ensity)J%nletH'in.D2H1=m>H0*1=m>
c&@&i.tK4enom
c4@4ra3K4enom
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Workshop Supplement %onitors
1. dit -utput Control 'ro# the -utline tree and go to the $onitor ta$
2. *hec the $onitor -ptions $o)!. *lic on the Add ew Ite# icon and na#e it C&
+. Set the -ption to !pression and enter c&
– %his is the #onitor point 'or the *oe''icient o' 6i't. Note that all na#es and
e)pressions are case sensitive, so the #onitor point is na#ed ?*6@ and it
re'ers to the e)pression na#ed ?c6@.:. Add a ne( ite# called C4 and set it to the e)pression c4
– %his is the *oe''icient o' "rag
/. *lic -/
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Workshop Supplement "olver Control
<pen the Soler Control section 'ro# the
<&tline tree
1. Increase the $a!* %terations to 200
2. *hange the Timescale Factor 'ro# 1 to 10
– A larger ti#escale can accelerate
convergence, $&t too large a ti#escale (ill
ca&se the solver to 'ail
!. Set the esidual Tar3et to 1eE:
– %his is a tighter convergence criteria and is
disc&ssed '&rther $elo(
+. *lic -/
:. %his case is no( ready to r&n so clic onFile , Sae "ro#ect then close the *7;-Pre
(indo( to ret&rn to the #ain Wor$ench
(indo(
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Workshop Supplement *unnin+ the "i'ulation
1. In Wor$ench right-clic on Solution and select 'pdate
2. A'ter the solver has started right-clic on Solution again and select4isplay $onitors
– %his (ill open the Solver anager and allo( the resid&als and #onitors to
$e vie(ed
!. *hec thro&gh all o' the resid&als and #onitor val&es. %he val&es o' *"
and *6 $eco#e steady a'ter a$o&t :0 iterations. Yo& can clic the Stop
$&tton 'ro# the tool$ar to stop the r&n at this point.
In the Solver anager the 'ser "oints ta$ displays the #onitor points set&p
in the -utput Control section o' *7; Pre. %his (ill incl&de the val&es o' C& and C4. %hese sho&ld converge to a steady val&e $e'ore the convergence
criteria is #et. <ther(ise the r&n sho&ld $e e)tended. any cases (ill $e
converged (hen an S resid&al level o' 1e-+ is reached. 7or this case this
is inadeJ&ate since the li't and drag had not reached steady val&es (hen
the resid&als (ere at 1e-+, hence a tighter convergence criteria (as &sed.
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Workshop Supplement %onitor ,alues
Ke'ore e)iting the Solver anager the
converged val&es o' *6 and *" can $e
vie(ed $y clicing on the #onitor lines.
%he val&es e)tracted sho&ld $e *6G0.2!/
and *"G0.0052. %hese val&es co#pare
(ell to p&$lished val&es o' *6G0.2+1 and*"G0.00.
No( close the solver and ret&rn to the
Wor$ench (indo(.
AIAA-5-0+1/ N&#erical Si#&lation o' =isco&s %ransonic Air'oil 7lo(s 15. %ho#as L
*oaley, NASA AS esearch *entre.
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Workshop Supplement -ostprocessin+
1. ight-clic in the esults cell and select
dit to open *7"-Post. %he res<s
sho&ld a&to#atically $e loaded
%his case reJ&ired a large do#ain to
allo( the $o&ndary conditions to $e
i#posed (itho&t a large arti'icial
restriction on the 'lo(. 8o(ever d&ring
post-processing the #ain interest (ill $e
in the 'lo( close to the air'oil.
2. *lic on the >-a)is in the $otto# right
corner o' the =ie(er to orientate the vie(
!. Bse the $o) Moo# 3right #o&se $&tton4
so the =ie(er displays the region aro&nd
the air'oil
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Workshop Supplement -ostprocessin+
When looing at the 'lo( aro&nd an air'oil,
plots o' several varia$les can $e o' interest
s&ch as velocity, press&re and ach n&#$er.
1. In the tree t&rn on the visi$ility o' Sym &e.t $y
clicing in the chec $o)
2. "o&$le-clic on Sym &e.t to $ring &p thedetails section
!. Bnder the Colour ta$ change the #ode to
ariale and select elocity &sing the +loal
ange, then clic Apply
Notice that the #a)i#&# velocity is aro&nd
!:0 D#sE. %his is higher than the sonic speed
o' !+0 D#sE calc&lated earlier 'or 'ree-strea#
conditions.
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Workshop Supplement -ostprocessin+
%o plot the ach n&#$er a conto&r plot (ill
$e &sed so the s&personic region can clearly
$e identi'ied.
1. Select %nsert , Contour or clic on the conto&r
icon
2. Accept the de'a< na#e then set &ocations toSym &e.t and the ariale to $ach umer
!. *hange the an3e to 'ser Speci.ied and
enter 0 to 1*1 as the range
+. Set L o. Contours to 12 , then clic Apply
:. %&rn o' the =isi$ility o' Sym &e.t so that theprevio&s velocity plot is hidden
/. %ry plotting other varia$les s&ch as Press&re
or "ensity, &se the 6ocal or Hlo$al ange
(hen li#its are not no(n
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Workshop Supplement -ostprocessin+
%o plot the press&re coe''icient distri$&tion aro&nd the air'oil a
polyline is needed to represent the air'oil pro'ile and a varia$le
needs to $e created to give *P.
1. *reate a Polyline &sing &ocation , "olyline 'ro# the tool$ar
2. *hange the $ethod to 8oundary %ntersection
!. Set 8oundary &ist to Air.oil +. Set %ntersect With to Sym &e.t and then clic Apply
:. %&rn o'' visi$ility o' the previo&s created *onto&r plot to see the
Polyline
A line (ill $e created aro&nd one end o' the air'oil. 7or '&ll !" cases
;Y planes can $e create at vario&s span locations and &sed to
e)tract Polylines.
WS2 Fl Ai f il
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Workshop Supplement -ostprocessin+
:. ove to the !pressions ta$ and right-clic to create a ne(
e)pression na#ed c" (ith the de'inition
"ressureK(0*9HmassFlowAe(4ensity)J%nletH'in.D2)
/. ove to the ariales ta$ and right-clic to create a ne( varia$le
na#ed C" .
. Set the $ethod to !pression and select c" . *lic -/ .
WS2 Fl Ai f il
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Workshop Supplement -ostprocessin+
A chart sho(ing the press&re distri$&tion aro&nd the air'oil (ill no( $e
created.
1.Insert a chart &sing %nsert , Chart or selecting
2.In the +eneral ta$ leave the type as XM
!.ove to the 4ata Series ta$ and enter a ne( series. Set the location to
"olyline 1
+.ove to the X A!is ta$ and change the varia$le to X
:.ove to the M A!is ta$ and change the varia$le to C"
/.*lic Apply and the chart is generated
%hese val&es can $e co#pared (ith e)peri#ental res<s.
AIAA-5-0+1/ N&#erical Si#&lation o' =isco&s %ransonic Air'oil 7lo(s 15. %ho#as L *oaley, NASA AS esearch *entre.
WS2 Fl Ai f il
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Workshop Supplement -ostprocessin+
. et&rn to the 4ata Series ta$ and change the
na#e to CFX
5. Insert a ne( series and give it the na#e
!periment
. *hange the 4ata Source to File and select the
'ile C"*cs
10. <n the &ine 4isplay ta$, set &ine Style toone and Symols to ectan3le. Also ens&re
that Symol Colour is a di''erent colo&r 'ro#
the c&rrently plotted *7; line
11. *lic Apply and $oth data series are dra(n
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WS2: Flow over an Airfoil
WS2-2/ ANSYS, Inc. Proprietary
© 2010 ANSYS, Inc. All rights reserved.elease 1!.0
"ece#$er 2010
Workshop Supplement "u''ar)
%he (orshop has covered
O 6oading an e)isting #esh
O Scaling the #esh
O Henerating Ne( egions 'ro# e)isting 2" Pri#itives
O Setting &p and r&nning a high speed co#pressi$le 'lo( si#&lation over
an air'oil
O )tracting li't and drag 'orces and co#paring (ith e)peri#ental data
O )a#ining the 'lo( patterns aro&nd the air'oil
O *o#paring the press&re distri$&tion to e)peri#ental val&es
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WS2: Flow over an Airfoil
ANSYS Inc Proprietary elease 1! 0
Workshop Supplement "cope for further work.
%his si#&lation is a good #atch to e)peri#ental (or $&t '&rther steps
co&ld $e taen i' reJ&ired, incl&ding
O e'ining the #esh, partic&larly in the (ae region.
O Applying a transition #odel to acco&nt 'or the s#all region o' la#inar 'lo(
aro&nd the nose o' the air'oil.
O Adding additional air'oil 'eat&res s&ch as a 'inite thicness trailing edgethat (ill $e &sed on all ?real air'oils@.
O Si#&lating the (hole (ing to acco&nt 'or span(ise variations.
Adding #ore 'eat&res to a si#&lation (ill &s&ally increase the
co#p&tational cost, so one o' the #ost i#portant step in any si#&lation is
to decide (hich 'eat&res need to $e incl&ded and (hich can $e le't o&t.