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AerodynamicsB, AE2115 I, Chapter II

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Angular Velocity, Vorticity and Strain. Circulation. Stream Function. Velocity Potential ... Vorticity & Strain. Different aspects of the movement of a particle: ... – PowerPoint PPT presentation

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Title: AerodynamicsB, AE2115 I, Chapter II


1
Aerodynamics Some Fundamental Principles and
Equations
  • Dr.ir. M.I. Gerritsma Dr.ir. B.W. van
    Oudheusden
  • Delft University of Technology
  • Department of Aerospace Engineering
  • Section Aerodynamics

2
Continuity Equation, Differential Form
  • We already found that

Remember that V and V are fixed in space,
therefore
Apply divergence theorem
So the continuity equation becomes
3
Continuity Equation, Differential Form
  • This equation holds for any arbitrary volume V

If this holds for every imaginable volume V, then
the integrand must be zero, so
Validity 3D, time-dependent, viscous-inviscid,
(in)compressible, allows for discontinuous
solutions (!?)
Stationary flows
4
Continuity Equation, Differential Form
  • Conservative formulation
  • Non-conservative formulation

5
Physical Meaning of the Divergence of Velocity
  • Moving control volume
  • Constant mass
  • Shape changes

6
Physical Meaning of the Divergence of Velocity
  • Assume that the volume VV is so small that
    is constant in V, then

is physically the time rate of change of
the volume of a moving fluid element, per unit
volume
7
Momentum Equation
  • Newtons second Law

Physical Principle Force time rate of change
of momentum.
Note and are vectors, so the above
identity has to hold for each component.
  • 1. Body Forces
  • Gravity
  • Electromagnetic forces
  • Coriolis forces

Which types of forces act on a fluid?
  • 2. Surface forces
  • normal stresses (perpendicular to plane)
  • tangential forces (along the plane)

8
Body Forces
Fixed control volume V
Assume is the body force per unit mass
exerted on fluid inside V
The body force acting on a small volume dV
Total force on volume
Example, gravity
9
Pressure contribution
  • Consider a small elementary surface
  • On this surface the pressure p acts, therefore
  • in the opposite direction of the outward unit
    normal
  • Therefore the total pressure force on V equals

10
Viscous forces
  • The viscous forces are simply denoted by
    . In Aerodynamics-D AE3-130 explicit formulae for
    will be given.

We want to find an expression for
  • Consists of
  • Body forces
  • Pressure forces
  • Viscous forces

Therefore
11
  • We want to find an expression for

Question How do we evaluate the rate of change
of momentum in the volume V?
  • Answer 2 contributions G and H
  • G Net flow of momentum out of control volume
    across surface S.
  • H Time rate of change of momentum due to
    unsteady fluctuations of flow properties inside V

G Recall that the mass flow across the elemental
area ds is given by Hence, the flow of momentum
per second across ds is Integrating over the
whole surface yields Note that when Ggt0 momentum
is flowing out of the control volume.
12
  • H Time rate of change of momentum due to
    unstaedy phenomena in V.

Question What is the total amount of momentum in
V at time t.
Answer Within a small volume element dV with
velocity and mass
Therefore the time rate of change of momentum in
the volume V is given by
13
Integral form of the momentum equation
  • Newton

Therefore
Body forces
Pressure forces
Viscous forces
Momentum transport across surface
Rate of change of momentum in V
14
Some Remarks concerning the Momentum Equation
  • The momentum equation is a vector equation. In
    fact we have three separate equations in the
    x-direction, y-direction and z-direction.
  • The integral equation is valid for unsteady,
    viscous, (in)compressible, three dimensional
    flows.
  • will be treated separately
    (Aerodynamics-D AE3-130)
  • The integral formulation only provides
    information over integrated quantities, so no
    local values of density, pressure, temperature,
    etc, can be extracted.

Conversion to differential form
  • Recipe
  • Convert all surface integrals to volume
    integrals using the integral relations given in
    section 2.2.11.
  • Interchange and which is allowed
    since V is fixed in space.
  • Collect all integrands underneath one integral
    and require that the integrand must vanish, since
    the integral holds for arbitrary volumes.

15
  • The momentum equation contains the surface
    integral
  • Apply the gradient theorem

In order to rewrite the convective surface
integral, we look at the x-component only
Take the x-component of the momentum equation
16
  • Apply divergence theorem to remaining surface
    integral (Convective term)

Writing the viscous force as
.
17
Additional Remarks
  • These equations are called the Navier-Stokes
    equations. They consist of a system of non-linear
    partial differential equations (PDEs).
  • The PDE connect the variables and the change in
    the variables locally.
  • If the flow is stationary,
    inviscid and there are no body
    forces we obtain the so-called Stationary Euler
    equations

18
Energy Equation
  • We have introduced now 5 unknowns,
    and we have only 4 equations, namely
    the three components of the momentum equation and
    the continuity equation.
  • We either have to add another equation, or remove
    one of the unknowns.
  • If the flow is incompressible, then the density
    is constant, so we can remove one unknown which
    closes the system
  • For compressible flows, one cannot remove any
    unknowns, therefore one has to add another
    equation. This will be the energy equation.
  • Physical Principle Energy cannot be created, nor
    destroyed.

First Law of Thermodynamics
Increment in internal energy
Work done on the system
Added heat
19
Energy Equation.
  • Apply to a control
    volume
  • Call
  • B1 the amount of heat added to the volume from
    the environment
  • B2 the amount of work exerted on the volume
  • B3 rate of change of energy as it flows
    through the control volume

B1 B2 B3
20
Determination of added heat B1
  • A small volume element dV receives from its
    environment an amount of heat per unit time and
    unit mass

So the total amount of heat added to dV per unit
time is
Sources are radiation, emission, combustion,
condensation, etc.
  • Through the surface V heat is added to the
    volume by conduction and mass diffusion. These
    are so-called viscous processes, denoted by

So the total heat added to the system, B1, will
be equal to
21
Rate of work done on the volume, B2
  • Work
  • On surface element a pressure force
    acts, so the amount of work per unit
    time due to the pressure will be
    So the
    total pressure contribution to the rate of work
    over the entire volume is given by
  • On dV a body force acts, therefore
    the rate of work due to the body force on dV is
    The total rate of work on V is
    given by
  • Viscous rate of work

22
Determination of the rate of change of energy, B3
  • Energy in V consists of internal energy, e per
    unit mass and kinetic energy per
    unit mass, so the total energy per unit mass is
    given by

At time t the amount of energy in dV is given by
So the instationary rate of change of energy
  • The rate of mass flowing through the surface
    carries a net amount of energy given by

23
Energy Equation
Thermal conduction, mass diffusion
Work done by body forces
Work done by pressure forces
Volumetric heating
Work done by viscous forces
Net rate of energy outflow
Transient fluctuations
  • This is the integral form of conservation of
    energy, valid for (in)compressible,
    viscous/inviscid fluids, stationary and time
    dependent problems.
  • Introduction of the enthalpie
  • Introduction of the total enthalpie

24
Energy Equation in terms of H
  • Total energy
  • total enthalpy

25
Differential Formulation of Energy Equation
  • Divergence Theorem
  • Results

26
Special Cases Energy Equation
  • If the flow is
  • stationary
  • inviscid
  • adiabatic
  • no body forces

27
Conclusion The change in H in the direction of
the flow is zero (remember directional
derivative), therefore H does not change in the
direction of the flow for a stationary,
inviscid, adiabatic flow without body forces the
total enthalpy is constant along streamlines!
28
Important Concepts in Aerodynamics
  • Substantial, Convective, Local Derivative,
  • Pathlines, Streamlines and Streaklines,
  • Angular Velocity, Vorticity and Strain
  • Circulation
  • Stream Function
  • Velocity Potential
  • Relationship between Stream Function and
    Velocity Potential

section 2.9 2.10 section 2.11 section
2.12 section 2.13 section 2.14 section
2.15 section 2.16
29
Substantial Derivative
  • When we consider a scalar quantity q we can
    either write this quantity with respect to fixed
    points in space, X, or with repect with a
    coordinate system that is moving with the flow,
    x.
  • Obviously, x, will be a function of time t, so
    x(t).
  • In the first case, we have the following time
    derivative
  • In the second case we have

30
Substantial Derivative
  • So we have the new time derivative
  • This can be written more succinctly as
  • The new time derivative is called the substantial
    or material time derivative

Convective Derivative
Substantial Derivative
Local Derivative
31
Fundamental Equations in terms of the Substantial
Derivative
  • Conservation of Mass
  • Conservation of Momentum
  • Conservation of Energy

32
Pathlines Streamlines
  • A pathline is the curve in space traced out by a
    particular particle in time
  • A streamline is a curve in space which is
    locally tangent to the velocity vector

For steady flows pathlines and streamline
coincide, for unsteady flows these lines are
generally different!
33
Direction of a Streamline
  • Since the curve is locally tangent to the
    velocity vector we have

Writing
So the equations for a streamline are
34
Vorticity Strain
  • Different aspects of the movement of a particle
  • The trajectory (already discussed)
  • Orientation (translation and rotation)
  • Deformation.
  • Rotation and deformation are determined by the
    velocity field.
  • Consider a 2 dimensional square

35
  • Convention counter clockwise rotations are
    positive
  • The angle is given by
  • and the rotation of AB by

36
  • Definition of angular velocity
  • The angular velocity of a small line element is
    given by
  • Therefore the angular velocity of AB is
  • And the angular velocity of AC is
  • The angular velocity of the fluid element ABCD
    is given by the average angular velocity

37
  • For general 3 dimensional flows the angular
    velocity is a vector given by

Vorticity is defined as
38
Irrotational Flow
  • If at every point in the flow,
    the flow is called rotational.
  • If at every point in the flow,
    the flow is called irrotational.

39
Irrotational Flow
  • Irrotational flow is of practical use
  • - Subsonic flow around airfoils
  • - Supersonic flow around slender bodies (no
    curved shock waves)
  • - Subsonic/Supersonic flow in nozzles, jets,
    wind tunnels, etc.

Note, that in many flows the flow outside the
boundary layer may be assumed to be irrotational,
but inside the boundary layer the flow is
rotational, since
40
Strain / Deformation
  • Strain is the change in k, where positive strain
    corresponds with decrasing strain

41
Time rate of strain
  • Definition Time rate of strain
  • Deformation rates!
  • Analogously

42
Circulation
  • Circulation is strongly connected to the notion
    of lift
  • Frederick Lanchaster (1878-1946)
  • Wilhelm Kutta (1867-1944)
  • Nicolai Joukowski (1847-1921)
  • Definition

  • Remarks
  • Circulation depends on the contour C chosen
  • It is customary to use a positive circulation in
    the clockwise direction!!

43
Connection between Circulation and Vorticity
  • The circulation of a flow around a closed curve C
    is by definition
  • Now using Stokes Theorem we get



44
Circulation and Vorticity
  • Stokes Theorem applied to circulation yields the
    following result
  • The circulation around a contour C can also be
    obtained by integrating the vorticity over the
    surface enclosed by this contour
  • Remarks
  • If everywhere (i.e. an
    irrotational flow) the circulation is zero for
    every contour C.
  • Conversely, if for every imaginable
    contour C, then the vorticity must be zero
    everywhere and therefore the flow will be
    irrotational.
  • Suppose that the contour shrinks such that it
    encloses a very small surface over which the
    vorticity is more or less constant, then the
    circulation is given by

45
Stream function
  • Consider a two dimensional flow
  • The definition of a streamline is given by

This equation constitutes a differential equation
with solution in which denotes the
integration constant. Each different constant
defines a different streamline. Suppose that
streamline A corresponds to the constant
and streamline B corresponds to
is called a stream function if
denotes the mass flow between the
streamlines A and B.
46
Stream function
  • Mass flow

Remark Differentiating the stream function in
the direction perpendicular to the streamline
produces the mass flux

47
Stream function
  • If the streamfunction is given, the above
    formulae give a way to determine the momentum per
    unit volume
  • Note that differentiation of the stream function
    in the y-direction produces the mass flux in the
    x-direction and vice versa.
  • For an incompressible flow we can redefine the
    streamfunction by setting by dividing by the
    constant density, in which case the above
    formulae produce the velocity components.
  • In polar coordinates the above equation become
  • The stream function provides a very usefull
    tool given the stream function we can
    immediately determine the streamlines by setting
    yconst and we can determine the velocity field
  • Note that the velocity components obtained from
    te stream function identically satisfy the
    stationary continuity equation.

48
Velocity Potential
  • The introduction of a velocity potential only
    makes sense for irrotational flows.
  • Irrotational
  • Vector identity
  • Therefore set


49
Potential Function
  • Remarks
  • If is given, the velocity
    components follow immediately by differentiation,
    so the potential function replace 3 unknowns u, v
    and w, by 1 unknown
  • The velocity component in a particular direction
    is obtained by differentiating the potential
    function in that particular direction.
  • By introducing the potential function we
    identically satisfy the condition for
    irrotational flow, i.e.
  • By replacing the velocity components by the
    gradient of the potential function in the
    continuity equation and momentum equation we
    obtain the so-called potential equation.
    Irrotational flows satisfying this equation are
    called potential flows.

50
Relation between the stream function and the
potential function
  • Consider a two dimensional, incompressible flow
  • Continuity equation
  • Streamlines
  • Equipotential lines

We know that is orthogonal to
the equipotential lines and oriented in the
direction of the flow so are the streamlines,
therefore equipotential lines are orthogonal to
the streamlines. A mathematical proof of this
assertion can be found in section 2.16.
51
Proof orthogonality of streamlines and
equipotential lines
  • Note that is perpendicular to the
    streamlines and is perpendicular to the
    equipotential lines, in which
  • so these gradients are perpendicular to
    eachother, and therefore the lines whose normals
    they are, are perpendicular as well.

52
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