Joukowsky transform +Search for Videos

In applied mathematics+, the '''Joukowsky transform''', named after Nikolai Zhukovsky+, is a conformal map+ historically used to understand some principles of airfoil+ design.

The transform is

: z=\zeta+\frac1\zeta,

where z=x+iy is a complex variable+ in the new space and \zeta=\chi + i \eta is a complex variable in the original space.
This transform is also called the '''Joukowsky transformation''', the '''Joukowski transform''', the '''Zhukovsky transform''' and other variations.

In aerodynamics+, the transform is used to solve for the two-dimensional potential flow+ around a class of airfoils known as Joukowsky airfoils. A '''Joukowsky airfoil''' is generated in the ''z-''plane by applying the Joukowsky transform to a circle in the \zeta plane. The coordinates of the centre of the circle are variables, and varying them modifies the shape of the resulting airfoil. The circle encloses the point \zeta = −1 (where the derivative is zero) and intersects the point \zeta = 1. This can be achieved for any allowable centre position \mu_x + i\mu_y by varying the radius of the circle.

Joukowsky airfoils have a cusp+ at their trailing edge+. A closely related conformal mapping, the '''Kármán–Trefftz transform''', generates the much broader class of Kármán–Trefftz airfoils by controlling the trailing edge angle. When a trailing edge angle of zero is specified, the Kármán–Trefftz transform reduces to the Joukowsky transform.

The Joukowsky transform of any complex number \zeta to z is as follows

z &= x + iy =\zeta+\frac1\zeta
&= \chi + i \eta + \frac1\chi + i \eta
&= \chi + i \eta + \frac(\chi - i \eta)\chi^2 + \eta^2
&= \frac\chi (\chi^2 + \eta^2 + 1)\chi^2 + \eta^2 + i\frac\eta (\chi^2 + \eta^2 - 1)\chi^2 + \eta^2.

So the real (''x'') and imaginary (''y'') components are:

x &= \frac\chi (\chi^2 + \eta^2 + 1)\chi^2 + \eta^2
\qquad \textand
y &= \frac\eta (\chi^2 + \eta^2 - 1)\chi^2 + \eta^2.

The transformation of all complex numbers on the unit circle is a special case.

:\sqrt\chi^2+\eta^2 = 1 \quad \textwhich gives \quad \chi^2+\eta^2 = 1.

So the real component becomes x = \frac\chi (1 + 1)1 = 2\chi
and the imaginary component becomes y = \frac\eta (1 - 1)1 = 0.

Thus the complex unit circle maps to a flat plate on the real number line from −2 to +2.

Transformation from other circles make a wide range of airfoil shapes.

The solution to potential flow around a circular cylinder+ is analytic+ and well known. It is the superposition of uniform flow+, a doublet+, and a vortex+.

The complex conjugate velocity \tildeW= \tildeu_x - i \tildeu_y, around the circle in the \zeta plane is

: \tildeW=V_\infty e^-i \alpha + \fraci \Gamma2 \pi (\zeta -\mu) - \fracV_\infty R^2 e^i \alpha(\zeta-\mu)^2

*\mu=\mu_x+i \mu_y is the complex coordinate of the centre of the circle
*V_\infty is the freestream velocity+ of the fluid
*\alpha is the angle of attack+ of the airfoil with respect to the freestream flow
*R is the radius of the circle, calculated using R=\sqrt(1-\mu_x)^2+\mu_y^2
*\Gamma is the circulation+, found using the Kutta condition+, which reduces in this case to

:: \Gamma=4\pi V_\infty R \sin \left(\ \alpha + \sin^-1 \left( \frac\mu_yR \right)\right).

The complex velocity ''W'' around the airfoil in the ''z-''plane is, according to the rules of conformal mapping and using the Joukowsky transformation:

: W=\frac\tildeW\fracdzd\zeta =\frac\tildeW1-\frac1\zeta^2.

Here W=u_x - i u_y, with u_x and u_y the velocity components in the x and y directions, respectively (z=x+iy, with x and y real-valued).
From this velocity, other properties of interest of the flow, such as the coefficient of pressure+ or lift+ can be calculated.

A Joukowsky airfoil has a cusp+ at the trailing edge.

The transformation is named after Russia+n scientist Nikolai Zhukovsky+. His name has historically been romanized in a number of ways, thus the variation in spelling of the transform.

The '''Kármán–Trefftz transform''' is a conformal map closely related to the Joukowsky transform. While a Joukowsky airfoil has a cusped trailing edge, a '''Kármán–Trefftz airfoil'''—which is the result of the transform of a circle in the ''ς''-plane to the physical ''z''-plane, analogue to the definition of the Joukowsky airfoil—has a non-zero angle at the trailing edge, between the upper and lower airfoil surface. The Kármán–Trefftz transform therefore requires an additional parameter: the trailing-edge angle ''α''. This transform is equal to:

z = n \frac\left(1+\frac1\zeta\right)^n+\left(1-\frac1\zeta\right)^n

with ''n'' slightly smaller than 2. The angle ''α'', between the tangent+s of the upper and lower airfoil surface, at the trailing edge is related to ''n'' by:

:\alpha = 2\pi\, -\, n\pi \quad \text and \quad n=2-\frac\alpha\pi.

The derivative dz/d\zeta, required to compute the velocity field, is equal to:

\fracdzd\zeta = \frac4n^2\zeta^2-1 \frac\left(1+\frac1\zeta\right)^n \left(1-\frac1\zeta\right)^n
\left[ \left(1+\frac1\zeta\right)^n - \left(1-\frac1\zeta\right)^n \right]^2.

First, add and subtract two from the Joukowsky transform, as given above:

z + 2 &= \zeta + 2 + \frac1\zeta\, = \frac1\zeta \left( \zeta + 1 \right)^2, \\
z - 2 &= \zeta - 2 + \frac1\zeta\, = \frac1\zeta \left( \zeta - 1 \right)^2.

Dividing the left and right hand sides gives:

\fracz-2z+2 = \left( \frac\zeta-1\zeta+1 \right)^2.

The right hand side+ contains (as a factor) the simple second-power law from potential flow+ theory, applied at the trailing edge near \zeta=+1. From conformal mapping theory this quadratic map is known to change a half plane in the \zeta-space into potential flow around a semi-infinite straight line. Further, values of the power less than two will result in flow around a finite angle. So, by changing the power in the Joukowsky transform—to a value slightly less than two—the result is a finite angle instead of a cusp. Replacing 2 by ''n'' in the previous equation gives:

\fracz-nz+n = \left( \frac\zeta-1\zeta+1 \right)^n,

which is the Kármán–Trefftz transform. Solving for ''z'' gives it in the form of equation (A).

In 1943 Hsue-shen Tsien+ published a transform of a circle of radius ''a'' into a symmetrical airfoil that depends on parameter ε and angle of inclination α:
:z = e^i \alpha (\zeta - \epsilon + \frac1\zeta - \epsilon + \frac2 \epsilon^2a + \epsilon).

The parameter ε yields a flat plate when zero, and a circle when infinite; thus it corresponds to the thickness of the airfoil.


* book
Fundamentals of Aerodynamics

* web
| first=D.W.
| last=Zingg
| title=Low Mach number Euler computations
| year=1989
| publisher=NASA+ TM-102205
| url=


Joukowsky transform+ In applied mathematics, the Joukowsky transform, named after Nikolai Zhukovsky, is a conformal map historically used to understand some principles of airfoil design.