Incompressible Irrotational Flow
Incompressible irrotational flow
Enrique Ortega [email protected] Rotation of a fluid element
As seen in M1_2, the arbitrary motion of a fluid element can be decomposed into
• A translation or displacement due to the velocity. • A deformation (due to extensional and shear strains) mainly related to viscous and compressibility effects. • A rotation (of solid body type) measured through the midpoint of the diagonal of the fluid element. The rate of rotation is defined as the angular velocity. The latter is related to the vorticity of the flow through: d 2 V (1) dt Important: for an incompressible, inviscid flow, the momentum equations show that the vorticity for each fluid element remains constant (see pp. 17 of M1_3).
Note that w is positive in the 2 – Irrotational flow counterclockwise sense Irrotational and rotational flow ij 0 According to the Prandtl’s boundary layer concept, thedomaininatypical(high-Re) aerodynamic problem at low can be divided into outer and inner
flow regions under the following considerations: Extracted from [1]. • In the outer region (away from the body) the flow is considered inviscid and irrotational (viscous contributions vanish in the momentum equations and =0 due to farfield vorticity conservation). • In the inner region the viscous effects are confined to a very thin layer close to the body (vorticity is created at the boundary layer by viscous stresses) and a thin wake extending downstream (vorticity must be convected with the flow). Under these hypotheses, it is assumed that the disturbance of the outer flow, caused by the body and the thin boundary layer around it, is about the same caused by the body alone. Therefore, the inner viscous region is neglected and the entire flow field is assumed inviscid and irrotational. This flow is called ideal flow and its solution is relatively simple and fairly accurate for most aerodynamic problems.
3 – Irrotational flow Some topological notions • Reducible curves: can be contracted to a point without leaving the region . • Simply connected region: a region where any closed curve is reducible. • Barrier: is a curve inserted into the region, but which is NOT part of the resulting modified region. The insertion of barriers can make a region simply connected. • Degree of connectivity: the number of barriers needed to make the region simply connected + 1.
reducible
barrier to
not reducible is now simply connected (degree 2). 4 – Irrotational flow Vorticity and circulation Considering a curve C enclosing a simply connected surface S in the flow field, by Stokes’ theorem it is possible to state Vn dS w n dS SScirculation V ds (2) C This can be illustrated by assuming a simple flow contained in the xy-plane
vu V duxvxs ()() y u y xv y C xy vu xy wdS vorticity = circulation / area S z xy
Note: by mathematical convention, the line integrals are positive in the counterclockwise direction. However, in aerodynamics it is convenient to consider positive in
Extracted from [2]. the clockwise sense.
5 – Irrotational flow Kelvin’s theorem: conservation of the circulation Kelvin’s theorem states that the circulation along a closed fluid curve in an inviscid, barotropic flow with conservative body forces remains constant with time, i.e.
DC D V ds 0 (3) Dt Dt C Note that Eq. (3) is similar to say that an irrotational flow remains irrotational if: • There is not net viscous forces along the path described by the fluid curve (this would cause diffusion of vorticity and, thus, changes in the circulation). • Conservative body forces (e.g. gravity) act through the center of mass of the fluid particle (there is no rotation; thus vorticity is not affected). • The flow is barotropic ( = const. or is a function of p only isentropic flow). For example, if depends on T, its gradient may cause rotation.
6 – Irrotational flow Generation of circulation
Extracted from [3]. Kelvin’s theorem does not impede that circulation can exist in the case of initially the latter is zero. Supposing an airfoil suddenly started
from rest, it is necessary for airfoil0 the existence of an additional circulation, generated at the starting moment (starting vortex), which makes that the total circulation does not change, i.e. it remains zero.
In Figure (b), the curve C2 is split into two loops, one enclosing the starting vortex and the other enclosing the airfoil. Circulation exists along these loops, but the total circulation remains zero; thus, Kelvin’s theorem is satisfied.
7 – Irrotational flow Irrotational flow and the velocity potential Considering the irrotational flow given in the figure, from Eq. (2) we have