Skip to main content

Streamlines

Streamlines: Streamlines represents field lines in a fluid flow. It is a path traced out by massless fluid particles moving with the flow, which is tangential to the instantaneous velocity direction. Different streamlines at same instant in a flow do not intersect or flow across it, because a fluid particle cannot have two different velocities at the same point.
For a unsteady flow, streamline pattern is different at different times because the velocity vectors are fluctuating with time both in magnitude and direction.
In a fluid flow, a bundle of streamlines is called a streamtube. Walls of an ordinary garden hose form a streamtube for the water flowing through the hose.
Differential equation for a streamline in two dimensions is \[vdx - udy = 0\]Question: x and y components of a velocity field are given as \(u = \frac{{4x}}{{\left( {{x^2} + {y^2}} \right)}}\) and \(v = \frac{{4y}}{{\left( {{x^2} + {y^2}} \right)}}\), what is the equation of streamlines.  
Solution: Equation of streamline is given as 
\(\left( {\frac{{dy}}{{dx}}} \right) = \left( {\frac{v}{u}} \right)\) therefore,
\(\left( {\frac{{dy}}{{dx}}} \right) = \frac{{\frac{{4y}}{{\left( {{x^2} + {y^2}} \right)}}}}{{\frac{{4x}}{{\left( {{x^2} + {y^2}} \right)}}}}\)
\(\left( {\frac{{dy}}{{dx}}} \right) = \frac{{4y}}{{\left( {{x^2} + {y^2}} \right)}} \times \frac{{\left( {{x^2} + {y^2}} \right)}}{{4x}}\)
\( = \left( {\frac{y}{x}} \right)\)
\(\frac{{dy}}{{dx}} = \frac{y}{x}\)
 \(\frac{{dy}}{y} = \frac{{dx}}{x}\) 
\(\ln y = \ln x + c\)
\(\ln y - \ln x = c\)
\(\ln \left( {\frac{y}{x}} \right) = \ln c\)
\(\frac{y}{x} = \ln c\)
\(y = {c_1}x\)
The streamlines are straight lines from a source.
Question: A velocity field has radial and tangential components of velocity as \({V_r} = 0\) and \({V_\theta } = 4r\).Obtain equation of streamlines.
Solution: Since  \({V_r} = 0,\),so there is no radial component of velocity.So the streamlines will be circular, with centres at origin.
\[\begin{array}{l}u =  - {v_\theta }\sin \theta \\ =  - 4r\sin \theta \\ =  - 4r\frac{y}{r} =  - 4y\\v = {v_{_\theta }}\cos \theta  = 4r\cos \theta  = 4r\frac{x}{r} = 4x\end{array}\] therefore equation of streamline\[\begin{array}{l}\left( {\frac{{dy}}{{dx}}} \right) = \frac{v}{u} = \left( {\frac{{ - x}}{y}} \right)\\ \Rightarrow ydy =  - xdx\\ \Rightarrow \frac{{{y^2}}}{2} + \frac{{{x^2}}}{2} = c\\ \Rightarrow {x^2} + {y^2} = {\rm{constant}}\end{array}\] This is equation of circle,with center at origin.
Question: Consider a velocity field where x and y components of velocity are given by u=4x and v=-4y. Obtain the equation of streamlines.
Solution:\[\begin{array}{l}\left( {\frac{{dy}}{{dx}}} \right) = \frac{v}{u} = \left( {\frac{{ - 4y}}{4x}} \right) = \left( {\frac{{ - y}}{x}} \right)\\ \Rightarrow \left( {\frac{{dy}}{y}} \right) = \left( {\frac{{ - dx}}{x}} \right)\\ \Rightarrow \ln y = x\ln x + c\\ \Rightarrow y = \frac{{{c_1}}}{x}\end{array}\]So,the streamlines are hyperbolas.

Comments

Popular posts from this blog

Non Lifting flow over a circular cylinder

When there is a superposition of a uniform flow with a doublet (Which is a source-sink pair of flows), a non-lifting flow over a circular cylinder can be analysed. Stream function \('\psi '\) for a uniform flow is \[\psi  = \left( {{V_\infty }r\sin \theta } \right)\left( {1 - \frac{{{R^2}}}{{{r^2}}}} \right)\] velocity field is obtained by differentiating above equation\[{V_r} = \left( {1 - \frac{{{R^2}}}{{{r^2}}}} \right){V_\infty }\cos \theta \]\[\,{\rm{and}}\,{{\rm{V}}_\theta } =  - \left( {1 + \frac{{{R^2}}}{{{r^2}}}} \right){V_\infty }\sin \theta \] Stagnation points can be obtained by equating \({V_r}\) and \({{\rm{V}}_\theta }\) to zero.Considering an incompressible and inviscid flow pressure coefficient over a circular cylinder is \[{C_p} = 1 - 4{\sin ^2}\theta \]Example: Calculate locations on the surface of a cylinder where surface pressure equals to free-stream pressure considering a non-lifting flow. Solution: Pressure coefficient ...

Bernoulli's equation

Euler's equation is given as \[dp =  - \rho vdv\]This equation applies to an incompressible and in-viscid flow where \(\rho  = \,{\rm{constant}}\). In a streamline, in between two points 1 and 2, the above Euler equation can be integrated as \[\int\limits_{{p_1}}^{{p_2}} {dp =  - \rho \int\limits_{{v_1}}^{{v_2}} {vdv} } \]\[{p_2} - {p_1} =  - \rho \left( {\frac{{v_2^2}}{2} - \frac{{v_1^2}}{2}} \right)\]\[ \Rightarrow {p_1} + \frac{1}{2}\rho v_1^2 = {p_2} + \frac{1}{2}\rho v_2^2\]This can be written as\[p + \frac{1}{2}\rho {v^2} = {\rm{constant}}\] for a streamline.For an rotational flow the value of constant is changing from streamline to another.For irrotational flow,the constant is same for all streamlines and \[p + \frac{1}{2}\rho {v^2} = {\rm{constant}}\]throughout the flow. Physical significance of Bernoulli's equation is that when the velocity increases, the pressure decreases  and when the velocity decreases, the pressure increases. ...

Importance of Coefficients (Lift and Drag)

Aerodynamic coefficients plays an important role in performance analysis as well as  design of aeroplanes.Coefficient of lift is defined as Lift divided by dynamic pressure, \(L/{q_\infty }S\) where as drag coefficient is defined as Drag divided by dynamic pressure, \(D/{q_\infty }S\) . Coefficient of lift,maximum or \({C_{L,\max }}\) is the determining factor for stalling velocity of aircraft.The higher is the \({C_{L,\max }}\) the lower is the stalling velocity.\[{V_{stall}} = \sqrt {\frac{{2W}}{{{\rho _\infty }S{C_{L,\max }}}}} \] However,\({C_{L,\max }}\) can be increased by the use of mechanical devices like high-lift devices.High lift devices include flaps,slats and slots on the wing. Air plane flying at given altitude with maximum thrust \({T_{\max }}\), the maximum value of \({V_\infty }\) ,corresponds to flight at \({C_{D,\min }}\).\[{V_{\max }} = \sqrt {\frac{{2{T_{\max }}}}{{{\rho _\infty }S{C_{D,\min }}}}} \] The actual value of \({C_L}\) and...