# MECH 221 FLUID MECHANICS (Fall 06/07) Chapter 7: INVISCID FLOWS

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MECH 221 FLUID MECHANICS (Fall 06/07) Chapter 7: INVISCID FLOWS
Instructor: Professor C. T. HSU

7.1 Inviscid Flow Inviscid flow implies that the viscous effect is negligible. This occurs in the flow domain away from a solid boundary outside the boundary layer at Re. The flows are governed by Euler Equations where , v, and p can be functions of r and t .

7.1 Inviscid Flow On the other hand, if flows are steady but compressible, the governing equation becomes where  can be a function of r For compressible flows, the state equation is needed; then, we will require the equation for temperature T also.

7.1 Inviscid Flow Compressible inviscid flows usually belong to the scope of aerodynamics of high speed flight of aircraft. Here we consider only incompressible inviscid flows. For incompressible flow, the governing equations reduce to where  = constant.

7.1 Inviscid Flow For steady incompressible flow, the governing eqt reduce further to where  = constant. The equation of motion can be rewrited into Take the scalar products with dr and integrate from a reference at  along an arbitrary streamline =C , leads to since

7.1 Inviscid Flow If the constant (total energy per unit mass) is the same for all streamlines, the path of the integral can be arbitrary, and in the flow domain except inside boundary layers. Finally, the governing equations for inviscid, irrotational steady flow are Since is the vorticity , flows with are called irrotational flows.

7.1 Inviscid Flow Note that the velocity and pressure fields are decoupled. Hence, we can solve the velocity field from the continuity and vorticity equations. Then the pressure field is determined by Bernoulli equation. A velocity potential  exists for irrotational flow, such that, and irrotationality is automatically satisfied.

7.1 Inviscid Flow The continuity equation becomes which is also known as the Laplace equation. Every potential satisfy this equation. Flows with the existence of potential functions satisfying the Laplace equation are called potential flow.

7.1 Inviscid Flow The linearity of the governing equation for the flow fields implies that different potential flows can be superposed. If 1 and 2 are two potential flows, the sum =(1+2) also constitutes a potential flow. We have However, the pressure cannot be superposed due to the nonlinearity in the Bernoulli equation, i.e.

7.2 2D Potential Flows If restricted to steady two dimensional potential flow, then the governing equations become E.g. potential flow past a circular cylinder with D/L <<1 is a 2D potential flow near the middle of the cylinder, where both w component and /z0. U L y x z D

7.2 2D Potential Flows The 2-D velocity potential function gives and then the continuity equation becomes The pressure distribution can be determined by the Bernoulli equation, where p is the dynamic pressure

7.2 2D Potential Flows For 2D potential flows, a stream function (x,y) can also be defined together with (x,y). In Cartisian coordinates, where continuity equation is automatically satisfied, and irrotationality leads to the Laplace equation, Both Laplace equations are satisfied for a 2D potential flow

7.2 Two-Dimensional Potential Flows
For two-dimensional flows, become: In a Cartesian coordinate system In a Cylindrical coordinate system and and

7.2 Two-Dimensional Potential Flows
Therefore, there exists a stream function such that in the Cartesian coordinate system and in the cylindrical coordinate system. The transformation between the two coordinate systems

7.2 Two-Dimensional Potential Flows
The potential function and the stream function are conjugate pair of an analytical function in complex variable analysis. The conditions: These are the Cauchy-Riemann conditions. The analytical property implies that the constant potential line and the constant streamline are orthogonal, i.e., and to imply that

7.3 Simple 2-D Potential Flows
Uniform Flow Stagnation Flow Source (Sink) Free Vortex

7.3.1 Uniform Flow For a uniform flow given by , we have Therefore,
Where the arbitrary integration constants are taken to be zero at the origin. and and

7.3.1 Uniform Flow This is a simple uniform flow along a single direction.

7.3.2 Stagnation Flow For a stagnation flow, Hence, Therefore,

7.3.2 Stagnation Flow The flow an incoming far field flow which is perpendicular to the wall, and then turn its direction near the wall The origin is the stagnation point of the flow. The velocity is zero there. x y

7.3.3 Source (Sink) Consider a line source at the origin along the z-direction. The fluid flows radially outward from (or inward toward) the origin. If m denotes the flowrate per unit length, we have (source if m is positive and sink if negative). Therefore,

7.3.3 Source (Sink) The integration leads to and
Where again the arbitrary integration constants are taken to be zero at and

7.3.3 Source (Sink) A pure radial flow either away from source or into a sink A +ve m indicates a source, and –ve m indicates a sink The magnitude of the flow decrease as 1/r z direction = into the paper. (change graphics)

7.3.4 Free Vortex Consider the flow circulating around the origin with a constant circulation . We have: where fluid moves counter clockwise if is positive and clockwise if negative. Therefore,

7.3.4 Free Vortex The integration leads to where again the arbitrary integration constants are taken to be zero at and

7.3.4 Free Vortex The potential represents a flow swirling around origin with a constant circulation . The magnitude of the flow decrease as 1/r.

7.4. Superposition of 2-D Potential Flows
Because the potential and stream functions satisfy the linear Laplace equation, the superposition of two potential flow is also a potential flow. From this, it is possible to construct potential flows of more complex geometry. Source and Sink Doublet Source in Uniform Stream 2-D Rankine Ovals Flows Around a Circular Cylinder

7.4.1 Source and Sink Consider a source of m at (-a, 0) and a sink of m at (a, 0) For a point P with polar coordinate of (r, ). If the polar coordinate from (-a,0) to P is and from (a, 0) to P is Then the stream function and potential function obtained by superposition are given by:

7.4.1 Source and Sink

7.4.1 Source and Sink Hence, Since We have

7.4.1 Source and Sink We have By Therefore,

7.4.1 Source and Sink The velocity component are:

7.4.1 Source and Sink

7.4.2 Doublet The doublet occurs when a source and a sink of the same strength are collocated the same location, say at the origin. This can be obtained by placing a source at (-a,0) and a sink of equal strength at (a,0) and then letting a  0, and m , with ma keeping constant, say 2am=M

7.4.2 Doublet For source of m at (-a,0) and sink of m at (a,0)
Under these limiting conditions of a0, m , we have

7.4.2 Doublet Therefore, as a0 and m with 2am=M
The corresponding velocity components are

7.4.2 Doublet

7.4.3 Source in Uniform Stream
Assuming the uniform flow U is in x-direction and the source of m at(0,0), the velocity potential and stream function of the superposed potential flow become:

7.4.3 Source in Uniform Stream

7.4.3 Source in Uniform Stream
The velocity components are: A stagnation point occurs at Therefore, the streamline passing through the stagnation point when The maximum height of the curve is

7.4.3 Source in Uniform Stream
For underground flows in an aquifer of constant thickness, the flow through porous media are potential flows. An injection well at the origin than act as a point source and the underground flow can be regarded as a uniform flow.

D Rankine Ovals The 2D Rankine ovals are the results of the superposition of equal strength sink and source at x=a and –a with a uniform flow in x-direction. Hence,

D Rankine Ovals Equivalently,

7.4.4 2-D Rankine Ovals The stagnation points occur at
where with corresponding

7.4.4 2-D Rankine Ovals The maximum height of the Rankine oval is
located at when ,i.e., which can only be solved numerically.

D Rankine Ovals rs ro

7.4.5 Flows Around a Circular Cylinder
Steady Cylinder Rotating Cylinder Lift Force

Steady Cylinder Flow around a steady circular cylinder is the limiting case of a Rankine oval when a0. This becomes the superposition of a uniform parallel flow with a doublet in x-direction. Under this limit and with M=2a. m=constant, is the radius of the cylinder.

Steady Cylinder The stream function and velocity potential become: The radial and circumferential velocities are:

Rotating Cylinder The potential flows for a rotating cylinder is the free vortex flow given in section Therefore, the potential flow of a uniform parallel flow past a rotating cylinder at high Reynolds number is the superposition of a uniform parallel flow, a doublet and free vortex. Hence, the stream function and the velocity potential are given by

Rotating Cylinder The radial and circumferential velocities are given by

Rotating Cylinder The stagnation points occur at From

Rotating Cylinder

Rotating Cylinder

7.4.5.2 Rotating Cylinder The stagnation points occur at Case 1:

Rotating Cylinder Case 1:

7.4.5.2 Rotating Cylinder Case 2:
The two stagnation points merge to one at cylinder surface where

7.4.5.2 Rotating Cylinder Case 3:
The stagnation point occurs outside the cylinder when where The condition of leads to Therefore, as , we have

Rotating Cylinder Case 3:

Lift Force The force per unit length of cylinder due to pressure on the cylinder surface can be obtained by integrating the surface pressure around the cylinder. The tangential velocity along the cylinder surface is obtained by letting r=ro,

Lift Force The surface pressure as obtained from Bernoulli equation is where is the pressure at far away from the cylinder.

Lift Force Hence, The force due to pressure in x and y directions are then obtained by

Lift Force The development of the lift on rotating bodies is called the Magnus effect. It is clear that the lift force is due to the development of circulation around the body. An airfoil without rotation can develop a circulation around the airfoil when Kutta condition is satisfied at the rear tip of the air foil. Therefore, The tangential velocity along the cylinder surface is obtained by letting r=ro: This forms the base of aerodynamic theory of airplane.

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