Surface Pressure Coefficient Distribution of a Doublet in a Uniform Flow

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SUMMARY

The discussion focuses on calculating the surface pressure coefficient distribution of a doublet in a uniform flow using complex potential flow theory. The key equation utilized is ##F=\phi+i\psi##, where ##\psi## represents the stream function. The user successfully decomposes the complex function to find ##\psi=U_{\infty}y-\frac {U_{\infty}R^2y} {x^2+y^2}##, which is essential for determining the velocity components at the boundary. The analysis concludes with the identification of two stagnation points at ##x=-R## and ##x=R##, confirming the behavior of the flow around the doublet.

PREREQUISITES
  • Understanding of complex potential flow theory
  • Familiarity with stream functions and their physical significance
  • Knowledge of doublets and their properties in fluid dynamics
  • Basic algebraic manipulation of complex numbers
NEXT STEPS
  • Study the implications of stagnation points in potential flow theory
  • Learn about the application of complex analysis in fluid dynamics
  • Explore the concept of surface pressure coefficients in various flow scenarios
  • Investigate the behavior of flow around different geometries, such as cylinders and airfoils
USEFUL FOR

Fluid dynamics students, engineers working on aerodynamic analysis, and researchers interested in potential flow theory will benefit from this discussion.

WhiteWolf98
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Homework Statement
A flow is defined by the complex potential:

##F=U_{\infty}(z+ \frac {R^2} {z})##

Show that the surface pressure coefficient distribution is given by:

##{C_p}=1-4\sin^{2}\theta##
Relevant Equations
##z=x+iy=re^{i\theta}##
##F=\phi+i\psi##
##\frac {dF} {dz}=u-iv##
So, it's a long way to the solution, but I'm finding it difficult to find a starting point. I'm going to say that as a first step, I should find what the value of the stream function ##\psi## is, at the surface. In order to do this, I need to use the following equation:

##F=\phi+i\psi##

If I can decompose ##F## into its real and imaginary parts, then I can find what ##\psi## is (##\psi=Im(F)##). I would just like to add that for a solid body, ##\psi=0##. In the case of a doublet in a uniform flow, you end up getting a flow around a circle. As no fluid passes through into this boundary, nor out of it (and it's a closed streamline), it can be see as a solid body and thus ##\psi## must be ##0##. I want to prove it anyway as this might be the case here, but perhaps not in a different case. My problem with decomposing ##F(z)## is the ##z## in the denominator. So you'd end up with:

##F(z)=U_{\infty}(z)+\frac {U_{\infty}R^2} {z}=U_{\infty}(x+iy)+\frac {U_{\infty}R^2} {x+iy}##

It's quite easy to know what to do with the first part ##(U_{\infty}x+iU_{\infty}y##), we quite nicely have a real and imaginary part there. But I've no clue what to do with the second part, where we have ##x+iy## in the denominator. Ultimately if I want pressure, I need to know what ##u## and ##v## are at the boundary (I'm assuming anywhere along the circle as no specific point has been given), and to know those I need to know what ##\psi## is.
 
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Does this help?
$$\frac 1{x+iy} \cdot \frac{x-iy}{x-iy} = \frac{x-iy}{x^2+y^2}$$
 
vela said:
Does this help?
$$\frac 1{x+iy} \cdot \frac{x-iy}{x-iy} = \frac{x-iy}{x^2+y^2}$$

I... think so, yes! So skipping all the algebra, the expression I end up with is:

##F(z)=U_{\infty}x+\frac {U_{\infty}R^2x} {x^2+y^2}+(U_{\infty}y-\frac {U_{\infty}R^2y} {x^2+y^2})i##​

As:

##\psi=Im(F)##
Then it would follow that:

##\psi=U_{\infty}y-\frac {U_{\infty}R^2y} {x^2+y^2}##
Now knowing what ##\psi## is, I'm able to find what its value (should be) at the stagnation points.

If:

##F(z)=U_{\infty}(z)+\frac {U_{\infty}R^2}{z}##​

Then:

##\frac {dF}{dZ}=U_{\infty}-\frac {U_{\infty}R^2}{z^2}##
At stagnation points:

##\frac {dF}{dZ}=0##​

Hence:

##U_{\infty}-\frac {U_{\infty}R^2}{z^2}=0##
Solving for ##z##:

##z=\pm R##​

If ##x_{st}+iy_{st}=\pm R##, then ##x_{st}=\pm R## and ##y_{st}=0##. Until this point, can I correctly say that there are two stagnation points at ##x=-R## and ##x=R##? I've done a little more, but it's probably best to break it into pieces rather than putting it down all in one go.
 

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