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Fluids – Lecture 16 Notes
- Vortex
- Lifting flow about circular cylinder
Reading: Anderson 3.14 – 3.
Vortex
Flowfield Definition A vortex flow has the following radial and tangential velocity components
C Vr = 0 , Vθ = r
where C is a scaling constant. The circulation around any closed circuit is computed as
θ (^2) C Γ ≡ − V · d~s = − Vθ r dθ = − r dθ = −C (θ 2 − θ 1 ) θ 1 r
y y
x
V
ds
d θ
r d θ
The integration range θ 2 −θ 1 = 2π if the circuit encircles the origin, but is zero otherwise.
− 2 πC , (circuit encircles origin) Γ = 0 , (circuit doesn’t encircle origin)
y y
(^12)
x
(^12)
x
In lieu of C, it is convenient to redefine the vortex velocity field directly in terms of the circulation of any circuit which encloses the vortex origin.
Γ Vθ = − 2 π r
1
x
A positive Γ corresponds to clockwise flow, while a negative Γ corresponds to counterclock- wise flow.
Cartesian representation The cartesian velocity components of the vortex are
u(x, y) =
2 π
y x^2 + y^2
v(x, y) = −
2 π
x x^2 + y^2
and the corresponding potential and stream functions are as follows.
φ(x, y) = −
2 π
arctan(y/x) = −
2 π
θ
ψ(x, y) =
2 π
ln
� x^2 + y^2 =
2 π
ln r
Singularity As with the source and doublet, the origin location (0, 0) is called a singular point of the vortex flow. The magnitude of the tangential velocity tends to infinity as
Vθ ∼
r
Hence, the singular point must be located outside the flow region of interest.
Lifting Flow over Circular Cylinder
Flowfield definition We now superimpose a uniform flow with a doublet and a vortex.
ψ = V∞ r sin θ
� 1 −
R^2
r^2
�
2 π
ln r
This corresponds to the flow about a circular cylinder of radius R as before, but now a top/bottom assymetry is introduced by the vortex.
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Using the cylinder geometry relations
nx = cos θ , ny = sin θ , dA = R dθ
and substituting the Cp(θ) result (1) gives
� Γ � (^2) π � 2 �^ � 1 1 �^2 π 2Γ cd = −Cp cos θ dθ = −1 + 4 sin^2 θ + + sin θ cos θ dθ 2 0 2 0 2 πV∞R πV∞R 1 �^2 π^1 �^2 π^ �^ Γ �^2 �^ 2Γ � cℓ = −Cp sin θ dθ = −1 + 4 sin^2 θ + + sin θ sin θ dθ 2 0 2 0 2 πV∞R πV∞R
After evaluating the integrals we obtain the final results.
cd = 0 Γ cℓ = V∞R
The equivalent dimensional forms are
D^ ′ = 0 (3) L^ ′ = ρ V ∞Γ^ (4)
The result of zero drag (3) is known as d’Alembert’s Paradox , since it’s in direct conflict with the observation that D′^ > 0 for all real bodies in a uniform flow. The explanation is of course that viscosity has been neglected. The lift result (4) is known as the Kutta-Joukowski Theorem, which will turn out to be valid for a 2-D body of any shape, not just for a circular cylinder.
Real Cylinder Flows
Real viscous flow about a circular cylinder at large Reynolds numbers exhibits large amounts of flow separation and drag. Normally the flow is symmetric between top and bottom, and hence the lift is zero. However, if the cylinder has a rotational velocity, the separation is pushed aft on the aft-going side and pushed forward on the forward-going side, resulting in a flow assymetry. This assymetry has an associated nonzero circulation and a corresponding lift. This phenomenon is known as the Magnus effect. Although the lift generated by a rotating cylinder can match or exceed the lift achievable by a wing of similar size, the cylinder is not a satisfactory lifting device because of its unavoidably large drag.
boundary layer separation
L’
A rotating sphere also exhibits the Magnus effect, and here it has a strong influence on many ball sports. The curveball pitch in baseball, the diving topspin volley in tennis, and the sideways curving flight of a sliced golf ball are all due to the Magnus effect.
