Potential flow

For potential flow around a cylinder, see Potential flow around a circular cylinder.

In fluid dynamics, potential flow or irrotational flow refers to a description of a fluid flow with no vorticity in it. Such a description typically arises in the limit of vanishing viscosity, i.e., for an inviscid fluid and with no vorticity present in the flow.

Potential-flow streamlines around a NACA 0012 airfoil at 11° angle of attack, with upper and lower streamtubes identified. The flow is two-dimensional and the airfoil has infinite span.

Potential flow describes the velocity field as the gradient of a scalar function: the velocity potential. As a result, a potential flow is characterized by an irrotational velocity field, which is a valid approximation for several applications. The irrotationality of a potential flow is due to the curl of the gradient of a scalar always being equal to zero.

In the case of an incompressible flow the velocity potential satisfies Laplace's equation, and potential theory is applicable. However, potential flows also have been used to describe compressible flows and Hele-Shaw flows. The potential flow approach occurs in the modeling of both stationary as well as nonstationary flows.

Applications of potential flow include: the outer flow field for aerofoils, water waves, electroosmotic flow, and groundwater flow. For flows (or parts thereof) with strong vorticity effects, the potential flow approximation is not applicable.

Description and characteristics

A potential flow is constructed by adding simple elementary flows and observing the result.

Streamlines for the incompressible potential flow around a circular cylinder in a uniform onflow.

In fluid dynamics, a potential flow is described by means of a velocity potential φ, being a function of space and time. The flow velocity v is a vector field equal to the gradient, ∇, of the velocity potential φ:

$\mathbf {v} =\nabla \varphi .$

Sometimes, also the definition v = −∇φ, with a minus sign, is used. But here we will use the definition above, without the minus sign. From vector calculus it is known that the curl of a gradient is equal to zero:

$\nabla \times \nabla \varphi =\mathbf {0} \,,$

and consequently the vorticity, the curl of the velocity field v, is zero:

$\nabla \times \mathbf {v} =\mathbf {0} \,.$

This implies that a potential flow is an irrotational flow. This has direct consequences for the applicability of potential flow. In flow regions where vorticity is known to be important, such as wakes and boundary layers, potential flow theory is not able to provide reasonable predictions of the flow. Fortunately, there are often large regions of a flow where the assumption of irrotationality is valid which is why potential flow is used for various applications. For instance in: flow around aircraft, groundwater flow, acoustics, water waves, and electroosmotic flow.

Incompressible flow

In case of an incompressible flow — for instance of a liquid, or a gas at low Mach numbers; but not for sound waves — the velocity v has zero divergence:

$\nabla \cdot \mathbf {v} =0\,,$

with the dot denoting the inner product. As a result, the velocity potential φ has to satisfy Laplace's equation

$\nabla ^{2}\varphi =0\,,$

where ∇² = ∇ ⋅ ∇ is the Laplace operator (sometimes also written Δ). In this case the flow can be determined completely from its kinematics: the assumptions of irrotationality and zero divergence of flow. Dynamics only have to be applied afterwards, if one is interested in computing pressures: for instance for flow around airfoils through the use of Bernoulli's principle.

In two dimensions, potential flow reduces to a very simple system that is analyzed using complex analysis (see below).

Compressible flow

Steady flow

Potential flow theory can also be used to model irrotational compressible flow. The derivation of the governing equation for $\varphi$ from Eulers equation is quite straightforward. The continuity and the (potential flow) momentum equations for steady flows are given by

$\rho \nabla \cdot \mathbf {v} +\mathbf {v} \cdot \nabla \rho =0,\quad (\mathbf {v} \cdot \nabla )\mathbf {v} =-{\frac {1}{\rho }}\nabla p=-{\frac {c^{2}}{\rho }}\nabla \rho$

where the last equation follows from that fact that entropy is constant for a fluid particle and that square of the sound speed is $c^{2}=(\partial p/\partial \rho )_{s}$. Eliminating $\nabla \rho$ from the two governing equations results in

$c^{2}\nabla \cdot \mathbf {v} -\mathbf {v} \cdot (\mathbf {v} \cdot \nabla )\mathbf {v} =0.$

The incompressible version emerges in the limit $c\to \infty$. Substituting here $\mathbf {v} =\nabla \varphi$ results in

$(c^{2}-\varphi _{x}^{2})\varphi _{xx}+(c^{2}-\varphi _{y}^{2})\varphi _{yy}+(c^{2}-\varphi _{z}^{2})\varphi _{zz}-2(\varphi _{x}\varphi _{y}\varphi _{xy}+\varphi _{y}\varphi _{z}\varphi _{yz}+\varphi _{z}\varphi _{x}\phi _{zx})=0$

where $c=c(v)$ is expressed as a function of the velocity magnitude $v^{2}=(\nabla \phi )^{2}$. For a polytropic gas, $c^{2}=(\gamma -1)(h_{0}-v^{2}/2)$, where $\gamma$ is the specific heat ratio and $h_{0}$ is the stagnation enthalpy. In two dimensions, the equation simplifies to

$(c^{2}-\varphi _{x}^{2})\varphi _{xx}+(c^{2}-\varphi _{y}^{2})\varphi _{yy}-2\varphi _{x}\varphi _{y}\varphi _{xy}=0.$

Validity: As it stands, the equation is valid for any inviscid potential flows, irrespective of whether the flow is subsonic or supersonic (e.g. Prandtl–Meyer flow). However in supersonic and also in transonic flows, shock waves can occur which can introduce entropy and vorticity into the flow making the flow rotational. Nevertheless, there are two cases for which potential flow prevails even in the presence of shock waves, which are explained from the (not necessairly potential) momentum equation written in the following form

$\nabla (h+v^{2}/2)-\mathbf {v} \times {\boldsymbol {\omega }}=T\nabla s$

where $h$ is the specific enthalpy, ${\boldsymbol {\omega }}$ is the vorticity field, $T$ is the temperature and $s$ is the specific entropy. Since in front of the leading shock wave, we have a potential flow, Bernoulli's equation shows that $h+v^{2}/2$ is constant, which is also constant across the shock wave (Rankine–Hugoniot conditions) and therefore we can write

$\mathbf {v} \times {\boldsymbol {\omega }}=-T\nabla s$

1) When the shock wave is of constant intensity, the entropy discontinuity across the shock wave is also constant i.e., $\nabla s=0$ and therefore vorticity production is zero. Shock waves at the pointed leading edge of two-dimensional wedge or three-dimensional cone (Taylor–Maccoll flow) has constant intensity. 2) For weak shock waves, the entropy jump across the shock wave is a third-order quantity in terms of shock wave strength and therefore $\nabla s$ can be neglected. Shock waves in slender bodies lies nearly parallel to the body and they are weak.

Nearly parallel flows: When the flow is predominantly unidirectional with small deviations such as in flow past slender bodies, the full equation can be further simplified. Let $U\mathbf {e} _{x}$ be the mainstream and consider small deviations from this velocity field. The corresponding velocity potential can be written as $\varphi =xU+\phi$ where $\phi$ characterizes the small departure from the uniform flow and satisfies the linearized version of the full equation. This is given by

$(1-M^{2}){\frac {\partial ^{2}\phi }{\partial x^{2}}}+{\frac {\partial ^{2}\phi }{\partial y^{2}}}+{\frac {\partial ^{2}\phi }{\partial z^{2}}}=0$

where $M=U/c_{\infty }$ is the constant Mach number corresponding to the uniform flow. This equation is valid provided $M$ is not close to unity. When $|M-1|$ is small (transonic flow), we have the following nonlinear equation

$2\alpha _{*}{\frac {\partial \phi }{\partial x}}{\frac {\partial ^{2}\phi }{\partial x^{2}}}={\frac {\partial ^{2}\phi }{\partial y^{2}}}+{\frac {\partial ^{2}\phi }{\partial z^{2}}}$

where $\alpha _{*}$ is the critical value of $\alpha =(c^{4}/2V^{3})(\partial ^{2}V/\partial p^{2})_{s}$ and $V=1/\rho$ is the specific volume. The transonic flow is completely characterized by the single parameter $\alpha _{*}$, which for polytropic gas takes the value $\alpha _{*}=(\gamma +1)/2$. Under hodograph transformation, the transonic equation in two-dimensions becomes the Euler–Tricomi equation.

Unsteady flow

The continuity and the (potential flow) momentum equations for unsteady flows are given by

${\frac {\partial \rho }{\partial t}}+\rho \nabla \cdot \mathbf {v} +\mathbf {v} \cdot \nabla \rho =0,\quad {\frac {\partial \mathbf {v} }{\partial t}}+(\mathbf {v} \cdot \nabla )\mathbf {v} =-{\frac {1}{\rho }}\nabla p=-{\frac {c^{2}}{\rho }}\nabla \rho =-\nabla h.$

The first integral of the (potential flow) momentum equation is given by

${\frac {\partial \varphi }{\partial t}}+{\frac {v^{2}}{2}}+h=f(t),\quad \Rightarrow \quad {\frac {\partial h}{\partial t}}=-{\frac {\partial \varphi }{\partial t}}-{\frac {1}{2}}{\frac {\partial v^{2}}{\partial t}}-g(t)$

where $f(t)$ and $g(t)=f'(t)$ are arbitrary functions. Without loss of generality, we can set $f(t)=g(t)=0$ since $\varphi$ is not uniquely defined. Combining these equations, we obtain

${\frac {\partial ^{2}\varphi }{\partial t^{2}}}+{\frac {1}{2}}{\frac {\partial v^{2}}{\partial t}}=c^{2}\nabla \cdot \mathbf {v} -\mathbf {v} \cdot (\mathbf {v} \cdot \nabla )\mathbf {v} .$

Substituting here $\mathbf {v} =\nabla \varphi$ results in

$\varphi _{tt}+{\frac {1}{2}}(\varphi _{x}^{2}+\varphi _{y}^{2}+\varphi _{z}^{2})_{t}=(c^{2}-\varphi _{x}^{2})\varphi _{xx}+(c^{2}-\varphi _{y}^{2})\varphi _{yy}+(c^{2}-\varphi _{z}^{2})\varphi _{zz}-2(\varphi _{x}\varphi _{y}\varphi _{xy}+\varphi _{y}\varphi _{z}\varphi _{yz}+\varphi _{z}\varphi _{x}\phi _{zx}).$

Nearly parallel flows: As in before, for nearly parallel flows, we can write (after introudcing a recaled time $\tau =c_{\infty }t$)

${\frac {\partial ^{2}\phi }{\partial \tau ^{2}}}+M{\frac {\partial ^{2}\phi }{\partial x\partial \tau }}=(1-M^{2}){\frac {\partial ^{2}\phi }{\partial x^{2}}}+{\frac {\partial ^{2}\phi }{\partial y^{2}}}+{\frac {\partial ^{2}\phi }{\partial z^{2}}}$

provided the constant Mach number $M$ is not close to unity. When $|M-1|$ is small (transonic flow), we have the following nonlinear equation

${\frac {\partial ^{2}\phi }{\partial \tau ^{2}}}+{\frac {\partial ^{2}\phi }{\partial x\partial \tau }}=-2\alpha _{*}{\frac {\partial \phi }{\partial x}}{\frac {\partial ^{2}\phi }{\partial x^{2}}}+{\frac {\partial ^{2}\phi }{\partial y^{2}}}+{\frac {\partial ^{2}\phi }{\partial z^{2}}}.$

Sound waves: In sound waves, the velocity magntiude $v$ (or the Mach number) is very small, although the unsteady term is now comparable to the other leading terms in the equation. Thus neglecting all quadratic and higher-order terms and noting that in the same approximation, $c$ is a constant (for example, in polytropic gas $c^{2}=(\gamma -1)h_{0}$), we have

${\frac {\partial ^{2}\varphi }{\partial t^{2}}}=c^{2}\nabla ^{2}\varphi ,$

which is a linear wave equation for the velocity potential φ. Again the oscillatory part of the velocity vector v is related to the velocity potential by v = ∇φ, while as before Δ is the Laplace operator, and c is the average speed of sound in the homogeneous medium. Note that also the oscillatory parts of the pressure p and density ρ each individually satisfy the wave equation, in this approximation.

Applicability and limitations

Potential flow does not include all the characteristics of flows that are encountered in the real world. Potential flow theory cannot be applied for viscous internal flows, except for flows between closely spaced plates. Richard Feynman considered potential flow to be so unphysical that the only fluid to obey the assumptions was "dry water" (quoting John von Neumann). Incompressible potential flow also makes a number of invalid predictions, such as d'Alembert's paradox, which states that the drag on any object moving through an infinite fluid otherwise at rest is zero. More precisely, potential flow cannot account for the behaviour of flows that include a boundary layer. Nevertheless, understanding potential flow is important in many branches of fluid mechanics. In particular, simple potential flows (called elementary flows) such as the free vortex and the point source possess ready analytical solutions. These solutions can be superposed to create more complex flows satisfying a variety of boundary conditions. These flows correspond closely to real-life flows over the whole of fluid mechanics; in addition, many valuable insights arise when considering the deviation (often slight) between an observed flow and the corresponding potential flow. Potential flow finds many applications in fields such as aircraft design. For instance, in computational fluid dynamics, one technique is to couple a potential flow solution outside the boundary layer to a solution of the boundary layer equations inside the boundary layer. The absence of boundary layer effects means that any streamline can be replaced by a solid boundary with no change in the flow field, a technique used in many aerodynamic design approaches. Another technique would be the use of Riabouchinsky solids.

Analysis for two-dimensional incompressible flow

Main article: Conformal map

Potential flow in two dimensions is simple to analyze using conformal mapping, by the use of transformations of the complex plane. However, use of complex numbers is not required, as for example in the classical analysis of fluid flow past a cylinder. It is not possible to solve a potential flow using complex numbers in three dimensions.

The basic idea is to use a holomorphic (also called analytic) or meromorphic function f, which maps the physical domain (x, y) to the transformed domain (φ, ψ). While x, y, φ and ψ are all real valued, it is convenient to define the complex quantities

${\begin{aligned}z&=x+iy\,,{\text{ and }}&w&=\varphi +i\psi \,.\end{aligned}}$

Now, if we write the mapping f as

${\begin{aligned}f(x+iy)&=\varphi +i\psi \,,{\text{ or }}&f(z)&=w\,.\end{aligned}}$

Then, because f is a holomorphic or meromorphic function, it has to satisfy the Cauchy–Riemann equations

${\begin{aligned}{\frac {\partial \varphi }{\partial x}}&={\frac {\partial \psi }{\partial y}}\,,&{\frac {\partial \varphi }{\partial y}}&=-{\frac {\partial \psi }{\partial x}}\,.\end{aligned}}$

The velocity components (u, v), in the (x, y) directions respectively, can be obtained directly from f by differentiating with respect to z. That is

${\frac {df}{dz}}=u-iv$

So the velocity field v = (u, v) is specified by

${\begin{aligned}u&={\frac {\partial \varphi }{\partial x}}={\frac {\partial \psi }{\partial y}},&v&={\frac {\partial \varphi }{\partial y}}=-{\frac {\partial \psi }{\partial x}}\,.\end{aligned}}$

Both φ and ψ then satisfy Laplace's equation:

${\begin{aligned}\Delta \varphi &={\frac {\partial ^{2}\varphi }{\partial x^{2}}}+{\frac {\partial ^{2}\varphi }{\partial y^{2}}}=0\,,{\text{ and }}&\Delta \psi &={\frac {\partial ^{2}\psi }{\partial x^{2}}}+{\frac {\partial ^{2}\psi }{\partial y^{2}}}=0\,.\end{aligned}}$

So φ can be identified as the velocity potential and ψ is called the stream function. Lines of constant ψ are known as streamlines and lines of constant φ are known as equipotential lines (see equipotential surface).

Streamlines and equipotential lines are orthogonal to each other, since

$\nabla \varphi \cdot \nabla \psi ={\frac {\partial \varphi }{\partial x}}{\frac {\partial \psi }{\partial x}}+{\frac {\partial \varphi }{\partial y}}{\frac {\partial \psi }{\partial y}}={\frac {\partial \psi }{\partial y}}{\frac {\partial \psi }{\partial x}}-{\frac {\partial \psi }{\partial x}}{\frac {\partial \psi }{\partial y}}=0\,.$

Thus the flow occurs along the lines of constant ψ and at right angles to the lines of constant φ.

Δψ = 0 is also satisfied, this relation being equivalent to ∇ × v = 0. So the flow is irrotational. The automatic condition ⁠∂²Ψ/∂x ∂y⁠ = ⁠∂²Ψ/∂y ∂x⁠ then gives the incompressibility constraint ∇ · v = 0.

Examples of two-dimensional incompressible flows

Main articles: Potential flow around a circular cylinder and Rankine half body

Any differentiable function may be used for f. The examples that follow use a variety of elementary functions; special functions may also be used. Note that multi-valued functions such as the natural logarithm may be used, but attention must be confined to a single Riemann surface.

Power laws

Examples of conformal maps for the power law w = Azⁿ

Examples of conformal maps for the power law w = Azⁿ, for different values of the power n. Shown is the z-plane, showing lines of constant potential φ and streamfunction ψ, while w = φ + iψ.

In case the following power-law conformal map is applied, from z = x + iy to w = φ + iψ:

$w=Az^{n}\,,$

then, writing z in polar coordinates as z = x + iy = re^iθ, we have

$\varphi =Ar^{n}\cos n\theta \qquad {\text{and}}\qquad \psi =Ar^{n}\sin n\theta \,.$

In the figures to the right examples are given for several values of n. The black line is the boundary of the flow, while the darker blue lines are streamlines, and the lighter blue lines are equi-potential lines. Some interesting powers n are:

• n = ⁠1/2⁠: this corresponds with flow around a semi-infinite plate,
• n = ⁠2/3⁠: flow around a right corner,
• n = 1: a trivial case of uniform flow,
• n = 2: flow through a corner, or near a stagnation point, and
• n = −1: flow due to a source doublet

The constant A is a scaling parameter: its absolute value |A| determines the scale, while its argument arg(A) introduces a rotation (if non-zero).

Power laws with n = 1: uniform flow

If w = Az¹, that is, a power law with n = 1, the streamlines (i.e. lines of constant ψ) are a system of straight lines parallel to the x-axis. This is easiest to see by writing in terms of real and imaginary components:

$f(x+iy)=A\,(x+iy)=Ax+iAy$

thus giving φ = Ax and ψ = Ay. This flow may be interpreted as uniform flow parallel to the x-axis.

Power laws with n = 2

If n = 2, then w = Az² and the streamline corresponding to a particular value of ψ are those points satisfying

$\psi =Ar^{2}\sin 2\theta \,,$

which is a system of rectangular hyperbolae. This may be seen by again rewriting in terms of real and imaginary components. Noting that sin 2θ = 2 sin θ cos θ and rewriting sin θ = ⁠y/r⁠ and cos θ = ⁠x/r⁠ it is seen (on simplifying) that the streamlines are given by

$\psi =2Axy\,.$

The velocity field is given by ∇φ, or

${\begin{pmatrix}u\\v\end{pmatrix}}={\begin{pmatrix}{\frac {\partial \varphi }{\partial x}}\\[2px]{\frac {\partial \varphi }{\partial y}}\end{pmatrix}}={\begin{pmatrix}+{\partial \psi \over \partial y}\\[2px]-{\partial \psi \over \partial x}\end{pmatrix}}={\begin{pmatrix}+2Ax\\[2px]-2Ay\end{pmatrix}}\,.$

In fluid dynamics, the flowfield near the origin corresponds to a stagnation point. Note that the fluid at the origin is at rest (this follows on differentiation of f(z) = z² at z = 0). The ψ = 0 streamline is particularly interesting: it has two (or four) branches, following the coordinate axes, i.e. x = 0 and y = 0. As no fluid flows across the x-axis, it (the x-axis) may be treated as a solid boundary. It is thus possible to ignore the flow in the lower half-plane where y < 0 and to focus on the flow in the upper halfplane. With this interpretation, the flow is that of a vertically directed jet impinging on a horizontal flat plate. The flow may also be interpreted as flow into a 90 degree corner if the regions specified by (say) x, y < 0 are ignored.

Power laws with n = 3

If n = 3, the resulting flow is a sort of hexagonal version of the n = 2 case considered above. Streamlines are given by, ψ = 3x²y − y³ and the flow in this case may be interpreted as flow into a 60° corner.

Power laws with n = −1: doublet

If n = −1, the streamlines are given by

$\psi =-{\frac {A}{r}}\sin \theta .$

This is more easily interpreted in terms of real and imaginary components:

${\begin{aligned}\psi ={\frac {-Ay}{r^{2}}}&={\frac {-Ay}{x^{2}+y^{2}}}\,,\\x^{2}+y^{2}+{\frac {Ay}{\psi }}&=0\,,\\x^{2}+\left(y+{\frac {A}{2\psi }}\right)^{2}&=\left({\frac {A}{2\psi }}\right)^{2}\,.\end{aligned}}$

Thus the streamlines are circles that are tangent to the x-axis at the origin. The circles in the upper half-plane thus flow clockwise, those in the lower half-plane flow anticlockwise. Note that the velocity components are proportional to r⁻²; and their values at the origin is infinite. This flow pattern is usually referred to as a doublet, or dipole, and can be interpreted as the combination of a source-sink pair of infinite strength kept an infinitesimally small distance apart. The velocity field is given by

$(u,v)=\left({\frac {\partial \psi }{\partial y}},-{\frac {\partial \psi }{\partial x}}\right)=\left(A{\frac {y^{2}-x^{2}}{\left(x^{2}+y^{2}\right)^{2}}},-A{\frac {2xy}{\left(x^{2}+y^{2}\right)^{2}}}\right)\,.$

or in polar coordinates:

$(u_{r},u_{\theta })=\left({\frac {1}{r}}{\frac {\partial \psi }{\partial \theta }},-{\frac {\partial \psi }{\partial r}}\right)=\left(-{\frac {A}{r^{2}}}\cos \theta ,-{\frac {A}{r^{2}}}\sin \theta \right)\,.$

Power laws with n = −2: quadrupole

If n = −2, the streamlines are given by

$\psi =-{\frac {A}{r^{2}}}\sin 2\theta \,.$

This is the flow field associated with a quadrupole.

Line source and sink

A line source or sink of strength $Q$ ($Q>0$ for source and $Q<0$ for sink) is given by the potential

$w={\frac {Q}{2\pi }}\ln z$

where $Q$ in fact is the volume flux per unit length across a surface enclosing the source or sink. The velocity field in polar coordinates are

$u_{r}={\frac {Q}{2\pi r}},\quad u_{\theta }=0$

i.e., a purely radial flow.

Line vortex

A line vortex of strength $\Gamma$ is given by

$w={\frac {\Gamma }{2\pi i}}\ln z$

where $\Gamma$ is the circulation around any simple closed contour enclosing the vortex. The velocity field in polar coordinates are

$u_{r}=0,\quad u_{\theta }={\frac {\Gamma }{2\pi r}}$

i.e., a purely azimuthal flow.

Analysis for three-dimensional incompressible flows

For three-dimensional flows, complex potential cannot be obtained.

Point source and sink

The velocity potential of a point source or sink of strength $Q$ ($Q>0$ for source and $Q<0$ for sink) in spherical polar coordinates is given by

$\phi =-{\frac {Q}{4\pi r}}$

where $Q$ in fact is the volume flux across a closed surface enclosing the source or sink. The velocity field in spherical polar coordinates are

$u_{r}={\frac {Q}{4\pi r^{2}}},\quad u_{\theta }=0,\quad u_{\phi }=0.$

See also

• Potential flow around a circular cylinder
• Aerodynamic potential-flow code
• Conformal mapping
• Darwin drift
• Flownet
• Laplacian field
• Laplace equation for irrotational flow
• Potential theory
• Stream function
• Velocity potential
• Helmholtz decomposition

References

• Batchelor, G.K. (1973), An introduction to fluid dynamics, Cambridge University Press, ISBN 0-521-09817-3
• Chanson, H. (2009), Applied Hydrodynamics: An Introduction to Ideal and Real Fluid Flows, CRC Press, Taylor & Francis Group, Leiden, The Netherlands, 478 pages, ISBN 978-0-415-49271-3
• Lamb, H. (1994) [1932], Hydrodynamics (6th ed.), Cambridge University Press, ISBN 978-0-521-45868-9
• Milne-Thomson, L.M. (1996) [1968], Theoretical hydrodynamics (5th ed.), Dover, ISBN 0-486-68970-0

Further reading

• Chanson, H. (2007), "Le potentiel de vitesse pour les écoulements de fluides réels: la contribution de Joseph-Louis Lagrange [Velocity potential in real fluid flows: Joseph-Louis Lagrange's contribution]", La Houille Blanche (in French), 93 (5): 127–131, doi:10.1051/lhb:2007072
• Wehausen, J.V.; Laitone, E.V. (1960), "Surface waves", in Flügge, S.; Truesdell, C. (eds.), Encyclopedia of Physics, vol. IX, Springer Verlag, pp. 446–778, archived from the original on 2009-01-05, retrieved 2009-03-29

External links

• "Irrotational flow of an inviscid fluid". University of Genoa, Faculty of Engineering. Retrieved 2009-03-29.
• "Conformal Maps Gallery". 3D-XplorMath. Retrieved 2009-03-29. — Java applets for exploring conformal maps
• Potential Flow Visualizations - Interactive WebApps