chapter 2 - cfd
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CFD Lectures, good for basic under standingTRANSCRIPT
National Key Laboratory of Science and Technology on Aerodynamic Design and Research
# Lecture 2 : The Governing Equations
Department of Fluid Mechanics, School of Aeronautics, Northwestern Polytechnical University, Xi’an, China
Presented by Zhonghua HanE-mail: [email protected]
29.03.2012
CFD Course for International Mixed Class
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Chapter 2 Governing Equations
2.1 Introduction All of CFD is based on the fundamental governing equations of fluid dynamics – the continuity, momentum and energy equations. These are corresponding to the fundamental physical principles as follows:
- Mass is conserved;
- Newton’s second law, F = ma;
- Energy is conserved.
The purpose of this chapter is to derive these equation. ☆
Why?
- You have no chance to be a CFD expert if you don’t know these equations
- Different forms of governing equations.23/4/28 2
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Partial differential equations of conservation form
Non-conservation form
Fundamental physical principles
Mass is conserved
Newton’s second law
Fixed finite control volume
Moving finite control volume
Fixed infinitesimally small volume
Moving infinitesimally small volume
Models of the flow
Forms of these equations particularly suited for CFD Boundary conditions: (a) Inviscid ; (b) Viscous
Energy is conserved
Non-conservation form Continuity equation
Momentum equations
Energy equation
Governing equations
Road Map for Chapter 2
Integral equations of conservation form
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2.2 Models of the Flow
To derive the basic equations of fluid motion, the following philosophy is always followed:
1. Choose the appropriate fundamental physical principle from the law of physics, such as - Mass is conserved; - Newton’s second law, F = ma; - Energy is conserved; ☆
2. Apply the fundamental physical principle to a suitable model of the flow;
3. Derive the mathematical equations, which embody these physical principles
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2.2.1 Finite Control Volume
② ① Fixed finite control volume
Moving finite control volume
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2.2.2 Infinitesimally Fluid Element
③ ④ Fixed infinitesimally small element
Moving infinitesimally small element
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☆ Different models of flow lead to different forms of governing equations
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2.2.3 Some Comments
- In general aerodynamic theory, whether we deal with
conservation or non-conservation forms of equations is irrelevant;
- One form can be obtained from the other, only through simple
mathematical manipulations;
- For CFD, it is important to choose the form of the equations. The
nomenclature distinguishing these two forms of equations is firstly
introduced by CFD researchers.
- …
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2.3 The Substantial Derivative (Time Rate of Change Following a Moving Fluid Element)
( ) ( ) ( )
( ) (higer-order terms)
x x y y z zx y z
t tt
2 1 2 1 2 1 2 11 11
2 11
),,,(),,,(),,,(
tzyxwwtzyxvvtzyxuu
kwjviuV
( , , , )( , , , )( , , , )
x y z tx y z tx y z t
1 1 1 1 1
2 2 2 2 2
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112
12
1
12
12
112
12
112
12
)()(
)()(
)()(
tttzz
z
ttyy
yttxx
xtt
DtD
tttt
12
12lim12
tz
wy
vx
uDtD
...
DT T T T Tu v wDt x y z t
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zw
yv
xu
tDtD
Definition of Substantial Derivative
zk
yj
xi
)(
VtDt
D Local derivative
( V ) Convective derivativet
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Substantial Derivative & Total Derivative
( ( ), ( ), ( ), )x t y t z t t
d x y zdt x t y t z t t
u v wx y z t
Vt
u v w
DDt
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DT
DV VV
1
Physical meaning: the time rate of change of volume of a moving fluid element, per unit volume
2.4 The Divergence of the Velocity: Its Physical Meaning
u v wVx y z
V ui vj wk
i j kx y z
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Net mass flow out of control volume through surface S
2.5 Continuity Equation
Physical principle: Mass is conserved
2.5.1 Model of the Finite Control volume Fixed in Space
time rate of decrease of mass inside the control volume
=
B = C
dS
V
dV
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S
B V dS
V
dVt
C
V S
dV V dSt
0
An integral form of the continuity equation A conservation form, derived from the flow model fixed in pace
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2.5.2 Model of the Finite Control Volume Moving with the Fluid
0V
dVDtD
dSnqdVt
dVDtD
bSVV
A frequently used formula :
bq
denotes the velocity the boundary :
An integral form of the continuity equationA nonconservation form
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2.5.3 Model of an infinitesimally Small Element Fixed in Space (Assignment)
0 V
t
2.5.4 Model of an infinitesimally Small Element Moving with the Fluid (Assignment)
0 VDtD
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2.5.5 All Equations Are One (Assignment) Four equations : 2 integral and 2 partial differential equations
or 2 conservation and 2 nonconservation forms
Four forms of the same equation.
2.5.6 Integral versus Differential Forms of Equations There is a subtle difference between the integral and differential forms of the governing equations:
- The integral form of the governing equations allows for the presence of discontinuities inside the fixed control volume.
- The differential form of the governing equations assumes the flow properties are differentiable.
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Apply Newton’s second law to the infinitesimally small element moving with the fluid (this model is particularly convenient ), in x direction:
xx maF
2.6 Momentum Equations
Physical principle: Newton’s second law, F= ma
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gravitational forceBody force
magnetic force
pressure F, , )Surface force
viscous, , , )xx yy zz
xy xz yz
normal stress(shear stress(
x x( body force ) f ( dxdydz ) ( 2.45)
Forces on a Moving Fluid Element
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Shear and Normal Stresses in Viscous Flows
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x(Net surface force) = [ ( ) ]
[( ]
[( ) ]
[(
xxxx xx
yxyx yx
zzx
pp p dx dydzx
dx ) dydzx
dy dxdzy
) ]xzxdz dxdy
z
( 2.46)
[ ]yxxx zxx x
pF dxdydz f dxdydzx x y z
( 2.47)
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xzxyxxx fzyxx
pDtDu
xDuma dxdydzDt
( 2.50a)
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zzzyzxz
yzyyyxy
xzxyxxx
fzyxz
pDtDw
fzyxy
pDtDv
fzyxx
pDtDu
For the infinitesimally small moving element, apply Newton’s second in x, y, z directions, respectively, one can obtain nonconservation differential equations :
( 2.50c)
( 2.50b)
( 2.50a)
Called Navier-Stokes equations in honor of two men: the French man M. Navier and the English man G. Stokes.
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Through mathematical manipulation, one can obtain the conservation differential momentum equations as follows
zzzyzxz
yzyyyxy
xzxyxxx
fzyxz
pVwtw
fzyxy
pVvtv
fzyxx
pVutu
)()(
)()(
)()(
( 2.56)
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( ) (2.57a)
( ) (2.57b)
( ) (2.57c)
(2.57e)
xx
yy
zz
xy yx
x
uVxvVywVz
v ux y
2
2
2
(2.57f)
(2.57g)
z zx
yz zy
u wz xv ux y
In the late of 17th century, Newton stated that shear stress in a fluid is proportional to the time rate of strain, i.e. velocity gradients. Such fluids are called Newtonian fluid. For such fluid, Stokes in 1845 obtained
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is the molecular viscosity coefficient and the second viscosity coefficient. Stokes made the hypothesis as
Substituting Eqs. ( 2.57) into (2.56), we obtain the complete Navier-Stokes equations in conservation form (to be continued):
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xfxw
zu
z
yu
xv
yxuV
x
xp
zuw
yuv
xu
tu
)(
)()2(
)()()()( 2
(2.58a)
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yfzv
yw
z
yvV
yyu
xv
x
yp
xvw
yv
xuv
tv
)(
)2()(
)()()()( 2
(2.58b)
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2
2 z
( w ) ( uw ) ( vw ) ( w ) pt x y z z
u w w v( ) ( )x z x y y z
w( V ) fz z
(2.58c)
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Physical principle: Energy is conserved
When applied to flow model of a fluid element moving with the flow, the first law states that
2.7 Energy Equations
Rate of change of energy inside fluid element
Net flux of heat into element
Rate of work done on element due to body and surface forces
= +
A = B + C
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( up ) ( up )up ( up dx ) dydz dxdydzx x
yx yxyx yx
( u ) ( u )( u dy ) u ) dxdz dxdydz
y y
zx zxzx zx
( u ) ( u )( u dz ) u ) dxdy dxdydzz z
xx xxxx xx
( u ) ( u )( u dx ) u ) dydz dxdydz
x z
- The net rate of work done by pressure in x direction ( adhe and bcgf) :
- The net rate of work done by normal stresses in x direction (adhe and bcgf) :
- The net rate of work done by shear stresses in x direction ( hefg and dabc) :
-The net rate of work done by shear stresses in x direction ( dcgh and abfe) :
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dxdydzVf
dxdydzz
wy
wx
w
zv
yv
xv
zu
yu
xu
zwp
yvp
xupC
zzyzxz
zyyyxy
zxyxxx
)()()(
)()()(
)()()()()()(
In total, the net rate of work done on the moving fluid element is the sum of the surface force contributions in x, y, z directions, as well as the body force contribution
( )pV
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xq dydz
Define as volumetric heat addition per unit mass. Note that the mass of the moving element is , we obtain:dxdydz
q
Volumentic heating of element = qdxdydz
The heat transferred by thermal conduction into the moving fluid element across face adhe is
is the heat transferred in the x direction per unit area by thermal conduction xq
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x xx x
q qq q dx dydz dxdydzx x
- =-
The heat transferred by thermal conduction into the moving fluid element across face bcgf is
xx
qq dx dydzx
Thus the net heat transferred in the x direction into the fluid element by thermal conduction is
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B yx zqq qq dxdydz
x y z
- + +
Taking into account heat transfer in the y and z directions across the other faces,
yx zqq q dxdydz
x y z
= - + +Heating of fluid element by thermal conduction
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dxdydzVeDtDA
2
2
The time rate change of total energy (internal and kinetic energy)
e The internal energy due to the random molecular motion
V 2
2 The kinetic energy due to the transitional motion of fluid element
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( ) ( ) ( )
( )( ) ( )( ) ( ) ( )
( ) ( ) ( )
yxxx zx
xy yy zy
D V T T Te q k k kDt x x y y z z
uu uup vp wpx y z x y z
v v vx y z
2
2
( )( ) ( ) yzxz zzww w f V
x y z
The final form of energy equation (nonconservation)
( 2.66)23/4/28 39
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( / ) (2.67)
( / ) (2.68)
yxxx zxx
xy yy zyy
D u pu u u u ufDt x x y z
D v pv v v v vfDt y x y z
2
2
2
2
( / ) (2.69)
yzxz zzz
D w pw w w w wfDt z x y z
2 2
To convert into one involving De/Dt , Multiply Eqs. ( 2.56a) 、 (2.56b) 、 (2.56c) by u 、 v, w, respectively.
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Through some manipulations, the energy equation can be simplified to
( ) ( ) ( )
( )
xx yx zx
xy yy zy
xz yz zz
De T T Tq k k kDt x x y y z z
u v w u u upx y z x y zv v vx y zw w wx y z
( 2.71)The kinetic energy and the body force terms have dropped out☆
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)()()(
)(
)()()(
yw
zv
xw
zu
xv
yu
zw
yv
xu
zw
yv
xup
zTk
zyTk
yxTk
xq
DtDe
zyzxyx
zzyyxx
( 2.72)
Since , , ,one can obtain
yx xy zx xz yz zy
Other forms in terms of enthalpy h and total enthalpy h0 can be obtained by similar manipulations
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( ) ( ) ( )
( ) ( )
( ) ( ) ( )
( ) ( ) ( )
De T T Tq k k kDt x x y y z z
u v w u v wpx y z x y z
u v wy y z
u v u w v wy x z x z y
2
2 2 2
2 2 2
2 2 2( 2.73)
Apply Eqs. (2.57a) to (2.72) in order to express the viscous stresses in terms of velocity gradient
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( ) ( ) ( ) ( ) ( )
( ) ( )
( ) ( ) ( )
e T T TeV q k k kt x x y y z z
u v w u v wpx y z x y z
u v wy y z
2
2 2 22 2 2
( ) ( ) ( )
u v u w v wy x z x z y
2 2 2
The energy equation can be written in conservation form:
( 2.79)
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The conservation form of energy equation in term of total energy:
( ) ( ) ( ) ( ) ( )
( ) ( ) ( )
V V T T Te e V q k k kt x x y y z z
up vp wpx y z
2 2
2 2
( )( ) ( )
( ) ( ) ( )
( )
yxxx zx
xy yy zy
xz
uu ux y z
v v vx y z
w
( ) ( )yz zzw w f V
x y z
( 2.81)
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2.8 Summary of the Governing Equations for Fluid Dynamics: with Comments
2.8.1 Navier-Stokes euqations
2.8.2 Euler Equations
2.8.3 Comments on the Governing Equations( 1 ) The y are coupled system of nonlinear partial differential equations,
and hence are very difficult to solve analytically. To date, there is no close-form solution to these equations.
( 2 ) For the momentum and energy equations, the differences between the nonconservation and conservation forms of the equations is just the left-hand side.
( 3 ) Note that the conservation forms of equations contain terms on the left-hand side which include the divergence of some quantity. For this reason, the conservation form of governing equations is sometimes called divergence form.
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( 4 ) The normal and shear stress terms in these equations are functions of the velocity gradients.
( 5 ) Examine the equations, we have 5 equations in terms if 7 unknown flow-field variables, . In aerodynamic, it is generally reasonable to assume that the gas is a perfect gas (which assume that intermolecular forces are negligible). For a perfect gas, the equations of state.
where R is the specific gas constant. A seventh equation to close the
entire system must be a thermodynamic relation between state variables. For example
For a calorically perfect gas (constant specific heats)
Tewvup ,,,,,,
RTp
Tce
pTee
v
),(
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( 6 ) Navier-Stokes equations are referred to as the whole system of equations in modern CFD, not only to the momentum equations for a viscous flow.
( 7 ) Similarly, Euler equations are referred to as the whole system of equations in modern CFD, not only to the momentum equations for a inviscid flow.
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2.9 Physical Boundary Conditions
Wall boundary :For viscous flow: non-slip condition, or zero relative velocity between the wall surface and the gas immediately at the wall
u=v=w=0
Boundary condition on the gas temperature : (1)
(2)
(3) Adiabatic wall
Inviscid flow: flow velocity adjacent to the wall must be tangent to the way
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( ) ww w
w
qT Tq k orn n k
0)(
wnT
0nV
T T w
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Other boundary conditions
- Outer flow: far-field boundary condition
- Internal flow: inflow and outflow
Numerical Boundary conditions
If the problem involves an aerodynamic body immersed in a known free stream, then the boundary conditions applied to a distance infinitely far upstream, above, blow and downstream of the body is simply the given free condition.
Numerically, due to the limitation of computational resource, the outer boundary of the computational domain has to be limited to a finite distance away from the wall boundary. In this case, the one-dimensional Riemann boundary condition is often applied.
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Other numerical boundary conditions:
- Symmetric
- periodic conditions
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( ) 0 wpn
Question: is this a boundary condition for solving of Navier-Stokes equations?
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2.10 Forms of the Governing Equations Particullay Suited for CFD: Comments on Conservation Form, Shock Fitting and Shock Capturing
The governing equations in conservation form can be written as
(2.93) JzH
yG
xF
tU
)2
(2Ve
wvu
U
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xzxyxx
xz
xy
xx
wvuxTkpuuVe
wuvu
pu
u
F
)2
(2
2
yzyyyx
yz
yy
xy
wvuyTkpvuVe
wvpv
uvv
G
)2
(2
2
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zzzyzx
zz
zy
zx
wvuzTkpwwVe
pwvwuww
H
)2
(2
2
qwfvfuffff
J
zyx
z
y
x
)(
0
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zzzyzx
zz
zy
zx
wvuzTkpwwVe
pwvwuww
H
)2
(2
2
qwfvfuffff
J
zyx
z
y
x
)(
0
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(2.99) zH
yG
xFJ
tU
Time-marching method
Flux variables & primitive variables
2)2/( 2222 wvuVee
ww
vv
uu
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Spatial marching methods, such as
(2.110) zH
yGJ
xF
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Benefit of using conservation form
- Numerically and computationally convenient;
- Generally more suited for CFD
Conservation Form of Governing Equations:
- Strong conservation form
- weak conservation form
Question : Conservation and non-conservation forms, which one is more suitable for flow with shock wave?
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Shock capturing and shock fitting methods:
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Hand on Practice
Use any existing code or software to simulate the
flow past an RAE 2822 airfoil at following flow
condition:
Ma = 0.729, al = 2.79, Re = 6.5E6
Assuming that this is an academic research project,
try to show me your capability as a scientist.
Make a presentation with sides no more than 10
and the results should be prepared according to the
standard required by top-level journal publication.
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xzxyxxx fzyxx
pDtDu
Added by 0)(
uV
t
)()(
)()(
)(
Vutu
uVut
uVtu
uVtDt
Du
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