Math 2.0

Fluid mechanics Aerodynamics Proposition

Biot–Savart law for vortex filaments

Builds on VorticityCirculationIncompressible flowVector fieldCurl

Statement

Let 𝐮\mathbf{u} be a smooth velocity vector field on ℝ3\R^3 with ∇⋅𝐮=0\nabla \cdot \mathbf{u} = 0, as in incompressible flow, and with 𝐮(x)→0\mathbf{u}(x) \to 0 as ∣x∣→∞\abs{x} \to \infty. Let its vorticity 𝝎=∇×𝐮\boldsymbol{\omega} = \nabla \times \mathbf{u}, the curl of 𝐮\mathbf{u}, have compact support. Then 𝐮(x)=14π∫ℝ3𝝎(y)×(x−y)∣x−y∣3 dyfor all x∈ℝ3.\mathbf{u}(x) = \frac{1}{4\pi} \int_{\R^3} \frac{\boldsymbol{\omega}(y) \times (x - y)}{\abs{x - y}^3}\, dy \quad \text{for all } x \in \R^3. Now let the vorticity be concentrated on an oriented smooth closed curve CC, a vortex filament with circulation Γ\Gamma. In this limit the induced velocity at a point x∉Cx \notin C is 𝐮(x)=Γ4π∮Cd𝐥(y)×(x−y)∣x−y∣3.\mathbf{u}(x) = \frac{\Gamma}{4\pi} \oint_C \frac{d\mathbf{l}(y) \times (x - y)}{\abs{x - y}^3}.

Remarks

The idea of the proof: since ∇⋅𝐮=0\nabla \cdot \mathbf{u} = 0, one can write 𝐮=∇×𝐀\mathbf{u} = \nabla \times \mathbf{A} with ∇⋅𝐀=0\nabla \cdot \mathbf{A} = 0, so −Δ𝐀=𝝎-\Delta \mathbf{A} = \boldsymbol{\omega}. Solving with the Newtonian potential gives 𝐀(x)=14π∫𝝎(y)∣x−y∣ dy\mathbf{A}(x) = \frac{1}{4\pi}\int \frac{\boldsymbol{\omega}(y)}{\abs{x - y}}\, dy, and taking the curl gives the formula. Uniqueness holds because the difference of two solutions is divergence-free, curl-free and decays at infinity, hence it is harmonic and zero. Example: for a straight infinite filament along the zz-axis, the formula gives the azimuthal speed Γ/(2πr)\Gamma / (2\pi r) at distance rr, the velocity of a point vortex. The filament formula diverges on the curve itself. The self-induced velocity of a curved filament grows like the logarithm of one over the core radius, so a real vortex needs a core of finite size.

Going deeper

For a student

The law recovers the velocity from the vorticity, which is the key step in vortex methods and in the vorticity form of the Euler equations. In aerodynamics it gives the downwash of the trailing vortices in lifting-line theory and the influence coefficients of the vortex lattice method. For a finite straight segment it can be integrated in closed form, which makes it cheap to evaluate for networks of straight vortex pieces.

Reading path

To understand this page from the ground up, read these 11 pages in order. The foundations come first.

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Each page uses the pages above it. The colour of the bar on a box shows how strong the evidence is, and the box also gives it as text. The list has the same pages.
  • no evidence level
  1. Circulation concept
  2. Euclidean space object
  3. Function concept
  4. Incompressible flow concept
  5. Vorticity concept
  6. Function of several variables concept
  7. Vector-valued function concept
  8. Partial derivative concept
  9. Vector field concept
  10. Curl concept
  11. Biot–Savart law for vortex filaments statement

Where this leads

2 pages build on this one.

Further reading

  1. Web https://en.wikipedia.org/wiki/Biot%E2%80%93Savart_law
About this page
TagZXKV1HSQMW
URIm2://ZXKV1HSQMW
Kindstatement, proposition
WritingW0 stub
MSC76B47, 76M23
StatusThis copy of the site has no build data. Run m2 status ZXKV1HSQMW.
AboutVorticity
UsesVorticity, Circulation, Incompressible flow, Vector field, Curl
Changed3 November 2026

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