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

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Presentation on theme: "1 MECH 221 FLUID MECHANICS (Fall 06/07) Chapter 7: INVISCID FLOWS Instructor: Professor C. T. HSU."— Presentation transcript:

1 1 MECH 221 FLUID MECHANICS (Fall 06/07) Chapter 7: INVISCID FLOWS Instructor: Professor C. T. HSU

2 MECH 221 – Chapter 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.

3 MECH 221 – Chapter 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.

4 MECH 221 – Chapter 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.

5 MECH 221 – Chapter 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

6 MECH 221 – Chapter 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 MECH 221 – Chapter 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.

8 MECH 221 – Chapter 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.

9 MECH 221 – Chapter 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.

10 MECH 221 – Chapter 7 10  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  D Potential Flows L D U x y z

11 MECH 221 – Chapter 7 11  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

12 MECH 221 – Chapter D 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

13 MECH 221 – Chapter Two-Dimensional Potential Flows  For two-dimensional flows, become: In a Cartesian coordinate system In a Cylindrical coordinate system and

14 MECH 221 – Chapter 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

15 MECH 221 – Chapter 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.

16 MECH 221 – Chapter Simple 2-D Potential Flows  Uniform Flow  Stagnation Flow  Source (Sink)  Free Vortex

17 MECH 221 – Chapter Uniform Flow and  For a uniform flow given by, we have  Therefore,  Where the arbitrary integration constants are taken to be zero at the origin.

18 MECH 221 – Chapter Uniform Flow  This is a simple uniform flow along a single direction.

19 MECH 221 – Chapter Stagnation Flow  For a stagnation flow,. Hence,  Therefore,

20 MECH 221 – Chapter 7 20  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 Stagnation Flow x  y

21 MECH 221 – Chapter 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,

22 MECH 221 – Chapter Source (Sink)  The integration leads to  Where again the arbitrary integration constants are taken to be zero at. and

23 MECH 221 – Chapter 7 23  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) Source (Sink)

24 MECH 221 – Chapter 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,

25 MECH 221 – Chapter Free Vortex and  The integration leads to where again the arbitrary integration constants are taken to be zero at

26 MECH 221 – Chapter 7 26  The potential represents a flow swirling around origin with a constant circulation .  The magnitude of the flow decrease as 1/r Free Vortex

27 MECH 221 – Chapter 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

28 MECH 221 – Chapter 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:

29 MECH 221 – Chapter Source and Sink

30 MECH 221 – Chapter Source and Sink  Hence,  Since  We have

31 MECH 221 – Chapter Source and Sink  We have  By  Therefore,

32 MECH 221 – Chapter Source and Sink  The velocity component are:

33 MECH 221 – Chapter Source and Sink

34 MECH 221 – Chapter 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

35 MECH 221 – Chapter 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

36 MECH 221 – Chapter Doublet  Therefore, as a  0 and m  with 2am=M  The corresponding velocity components are

37 MECH 221 – Chapter Doublet

38 MECH 221 – Chapter 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:

39 MECH 221 – Chapter Source in Uniform Stream

40 MECH 221 – Chapter 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

41 MECH 221 – Chapter 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.

42 MECH 221 – Chapter 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,

43 MECH 221 – Chapter D Rankine Ovals  Equivalently,

44 MECH 221 – Chapter D Rankine Ovals  The stagnation points occur at where with corresponding.

45 MECH 221 – Chapter D Rankine Ovals  The maximum height of the Rankine oval is located at when,i.e., which can only be solved numerically.

46 MECH 221 – Chapter D Rankine Ovals rsrs roro roro rsrs

47 MECH 221 – Chapter Flows Around a Circular Cylinder  Steady Cylinder  Rotating Cylinder  Lift Force

48 MECH 221 – Chapter 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.

49 MECH 221 – Chapter Steady Cylinder  The stream function and velocity potential become:  The radial and circumferential velocities are:

50 MECH 221 – Chapter Steady Cylinder roro

51 MECH 221 – Chapter 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

52 MECH 221 – Chapter Rotating Cylinder  The radial and circumferential velocities are given by

53 MECH 221 – Chapter Rotating Cylinder  The stagnation points occur at  From

54 MECH 221 – Chapter Rotating Cylinder

55 MECH 221 – Chapter Rotating Cylinder

56 MECH 221 – Chapter Rotating Cylinder  The stagnation points occur at Case 1: Case 2: Case 3:

57 MECH 221 – Chapter Rotating Cylinder  Case 1:

58 MECH 221 – Chapter Rotating Cylinder  Case 2:  The two stagnation points merge to one at cylinder surface where.

59 MECH 221 – Chapter Rotating Cylinder  Case 3:  The stagnation point occurs outside the cylinder when where. The condition of leads to  Therefore, as, we have

60 MECH 221 – Chapter Rotating Cylinder  Case 3:

61 MECH 221 – Chapter 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=r o,

62 MECH 221 – Chapter Lift Force  The surface pressure as obtained from Bernoulli equation is where is the pressure at far away from the cylinder.

63 MECH 221 – Chapter Lift Force  Hence,  The force due to pressure in x and y directions are then obtained by

64 MECH 221 – Chapter 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=r o :  This forms the base of aerodynamic theory of airplane.


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