Taylor–Culick flow

In fluid dynamics, Taylor–Culick flow describes the axisymmetric flow inside a long slender cylinder with one end closed, supplied by a constant flow injection through the sidewall. The flow is named after Geoffrey Ingram Taylor and F. E. C. Culick.^[1] In 1956, Taylor showed that when a fluid forced into porous sheet of cone or wedge, a favorable longitudinal pressure gradient is set up in the direction of the flow inside the cone or wedge and the flow is rotational; this is in contrast in the vice versa case wherein the fluid is forced out of the cone or wedge sheet from inside in which case, the flow is uniform inside the cone or wedge and is obviously potential. Taylor also obtained solutions for the velocity in the limiting case where the cone or the wedge degenerates into a circular tube or parallel plates. Later in 1966, Culick found the solution corresponding to the tube problem, in problem applied to solid-propellant rocket combustion.^[2] Here the thermal expansion of the gas due to combustion occurring at the inner surface of the combustion chamber (long slender cylinder) generates a flow directed towards the axis.

Flow description edit

The axisymmetric inviscid equation is governed by the Hicks equation, that reduces when no swirl is present (i.e., zero circulation) to

{\frac {\partial ^{2}\psi }{\partial r^{2}}}-{\frac {1}{r}}{\frac {\partial \psi }{\partial r}}+{\frac {\partial ^{2}\psi }{\partial z^{2}}}=-r^{2}f(\psi ),

where $\psi$ is the stream function, $r$ is the radial distance from the axis, and $z$ is the axial distance measured from the closed end of the cylinder. The function $f(\psi )=\pi ^{2}\psi$ is found to predict the correct solution. The solution satisfying the required boundary conditions is given by

\psi =aUz\sin \left({\frac {\pi r^{2}}{2a^{2}}}\right),

where $a$ is the radius of the cylinder and $U$ is the injection velocity at the wall. Despite the simple-looking formula, the solution has been experimentally verified to be accurate.^[3] The solution is wrong for distances of order $z\sim a$ since boundary layer separation at $z=0$ is inevitable; that is, the Taylor–Culick profile is correct for $z\gg 1$ . The Taylor–Culick profile with injection at the closed end of the cylinder can also be solved analytically.^[4]

Although the solution is derived for the inviscid equation, it satisfies the non-slip condition at the wall since, as Taylor argued, any boundary layer at the sidewall will be blown off by flow injection. Hence, the flow is referred to as quasi-viscous.

References edit

^ Taylor, G. I. (1956). Fluid flow in regions bounded by porous surfaces. Proceedings of the Royal Society of London. Series A. Mathematical and Physical Sciences, 234(1199), 456–475.
^ Culick, F. E. C. (1966). Rotational axisymmetric mean flow and damping of acoustic waves in a solid propellant rocket. AIAA Journal, 4(8), 1462–1464.
^ Dunlap, R., Willouchby, P. G., & Hermsen, R. W. (1974). Flowfield in the combustion chamber of a solid propellant rocket motor. AIAA journal, 12(10), 1440–1442.
^ Majdalani, J., & Saad, T. (2007). The Taylor–Culick profile with arbitrary headwall injection. Physics of Fluids, 19(9), 093601.

[1] Taylor, G. I. (1956). Fluid flow in regions bounded by porous surfaces. Proceedings of the Royal Society of London. Series A. Mathematical and Physical Sciences, 234(1199), 456–475.

[2] Culick, F. E. C. (1966). Rotational axisymmetric mean flow and damping of acoustic waves in a solid propellant rocket. AIAA Journal, 4(8), 1462–1464.

[3] Dunlap, R., Willouchby, P. G., & Hermsen, R. W. (1974). Flowfield in the combustion chamber of a solid propellant rocket motor. AIAA journal, 12(10), 1440–1442.

[4] Majdalani, J., & Saad, T. (2007). The Taylor–Culick profile with arbitrary headwall injection. Physics of Fluids, 19(9), 093601.

[1]

[2]

[3]

[4]

Taylor–Culick flow

Flow description edit

See also edit

References edit