Relationship between flow and pressure gradient in a one dimensional compressible fluid - Physics Stack Exchange most recent 30 from physics.stackexchange.com 2019-09-17T15:25:53Z https://physics.stackexchange.com/feeds/question/352406 https://creativecommons.org/licenses/by-sa/4.0/rdf https://physics.stackexchange.com/q/352406 1 Relationship between flow and pressure gradient in a one dimensional compressible fluid Foad https://physics.stackexchange.com/users/113880 2017-08-17T21:12:22Z 2019-08-22T10:00:31Z <p>Consider a one dimensional model (tube with diamter $D$) with a compressible viscose ($\mu$) fluid (e.g. air). further assumptions are</p> <ul> <li>conduction and radiation are negligible</li> <li>gravity's effect is negligible</li> <li>flow is one dimensional and uniform</li> <li>the flow is not steady-state so it is changing rapidly by time (e.g. Sod shock tube)</li> <li>gas is ideal $p=\rho \mathring{R} T$</li> </ul> <p>based on this assumptions it is possible to write conservation equations of mass, momentum and heat. However, solving those PDEs <a href="https://mathematica.stackexchange.com/questions/152721/solving-a-system-of-partial-differential-and-algebraic-equations-setting-the-st">is very difficult</a>. I'm looking for empirical equations to approximate the mass flow dependency on pressure gradient:</p> <p>$q= \rho \nu =f\left( \frac{\partial p}{\partial x},D,... \right)$</p> <p>I have looked into the literature but what I have found is mostly for steady state flow in long tubes (e.g. Weymouth and Panhandle Equations). I would appreciate if you could help me find such an approximate solutions for the said assumptions.</p> <p>P.S.1. I'm not interested in pressure loss. I have Darcy equation and its derivatives for that reason.</p> <p>P.S.2. I was not sure what tags to attache, so let me know please if they are irrelevant.</p> <p>P.S.3. I have found these equations from one article I'm reading:</p> <p><a href="https://i.stack.imgur.com/UMI2e.png" rel="nofollow noreferrer"><img src="https://i.stack.imgur.com/UMI2e.png" alt="enter image description here"></a></p> <p>But <a href="http://ieeexplore.ieee.org/abstract/document/4783211/" rel="nofollow noreferrer">the paper</a> has provided no reference or explanation where these equation came from, nor any name is mentioned. </p> https://physics.stackexchange.com/questions/352406/-/352514#352514 0 Answer by Foad for Relationship between flow and pressure gradient in a one dimensional compressible fluid Foad https://physics.stackexchange.com/users/113880 2017-08-18T13:06:07Z 2018-03-12T11:05:02Z <p>I think I have figured it out where the equations above come from. They are not empirical equation but approximations generated directly from conservation law of energy. It is also not for a tube in particular but rather for any 1 dimensional flow like orifice with cross section change (Venturi effect). Please do not consider this as the complete answer to the question but just explanation of how the equations mentioned in the said paper are generated.</p> <p>We will take a Lagrangian approach, so have a particle in mind. We have these further assumptions:</p> <ul> <li>process is reversible $\implies dS=\frac{dQ}{T}$, Where $S$ is entropy, and $Q$ is heat</li> <li>process is adiabatic so $dQ=0$, from first assumption it implies the process is isentropic too $\implies dS=0$</li> </ul> <p>The energy conservation law implies ( "Fluid Power Control by Blackburn 1960" page 68):</p> <p>$$h+\frac{v^2}{2}=k_1$$ </p> <p>where $h$ is the specific enthalpy and $v$ is speed. for ideal gas in isentropic process $h=c_P T$ :</p> <p>$$\implies c_PT+\frac{v^2}{2}=k_1$$</p> <p>for adiabatic process in ideal gas the polytropic equation boils down to:</p> <p>$$\frac{P}{\rho^\gamma}=k_2$$</p> <p>where $\gamma=\frac{c_P}{c_v}$ is the heat capacity ratio (above noted as $\kappa$) . For dry air is SI units $\gamma=1.4$, $C_p=1004$ and $\mathring{R}=286.9$</p> <p>$$\implies v=\sqrt{2\left(k_1-\frac{c_P\mathring{R}}{k_2^{\frac{1}{\gamma}}}P^{\left(1-\frac{1}{\gamma}\right)}\right)}$$</p> <p>$$\implies \dot{m}=\left(\frac{P}{k_2}\right)^{\frac{1}{\gamma}}\sqrt{2\left(k_1-\frac{c_P\mathring{R}}{k_2^{\frac{1}{\gamma}}}P^{\left(1-\frac{1}{\gamma}\right)}\right)}$$</p> <p>The number 0.528 comes from the equation for <a href="https://en.wikipedia.org/wiki/Choked_flow" rel="nofollow noreferrer">choked flow</a>:</p> <p>$$\frac{P_2}{P_1}=\left(\frac{2}{\gamma+1} \right)^{\left(\frac{\gamma}{\gamma -1} \right)}$$</p> <p>However I still don't know where this equation comes from. there are two options:</p> <ul> <li><p>Considering that the speed of flow can't be more than the speed of sound ($c=\sqrt{\gamma \mathring{R}T}$ for air $c\approx340$)</p></li> <li><p>from $\frac{\partial \dot{m}}{\partial P}=0$</p></li> </ul>