Waste gas \(\left(\mathrm{CO}_{2}\right)\) is vented to outer space from a spacecraft through a circular pipe \(0.2 \mathrm{m}\) long. The pressure and temperature in the spacecraft are \(35 \mathrm{kPa}\) and \(25^{\circ} \mathrm{C}\). The gas must be vented at the rate of \(0.01 \mathrm{kg} / \mathrm{s}\). The friction factor for the flow in the pipe is given by \\[\begin{array}{c}f=64 / \mathrm{Re}, \quad \mathrm{Re}<5000 \\\f=0.013, \quad \mathrm{Re}>5000, \quad \mathrm{Re}=\frac{ \dot{m}}{\pi \mu D}\end{array}\\] The viscosity \((\mu)\) is \(4 \times 10^{-4} \mathrm{N} \cdot \mathrm{s} / \mathrm{m}^{2}\). Determine the required pipe diameter.

Short Answer

Expert verified
The required pipe diameter can be found by iterating calculations based on Reynolds number and flow conditions, starting with assuming laminar flow. The answer will be validated when the resultant diameter gives a Reynolds number consistent with our flow condition assumption.

Step by step solution

01

Calculate initial Reynolds number

First, we need to estimate the Reynolds number to choose the correct friction factor.\[\mathrm{Re}=\frac{ \dot{m}}{\pi \mu D} \]But we don't know the diameter \(D\) of the pipe yet, so let's assume an initial Reynolds number value which is less than 5000 to start with. Let's assume that for that condition, the flow is laminar, so Re<5000.
02

Use the friction factor for laminar flow

Apply the friction factor formula for laminar flow (Re<5000) as follows: \[f=64 / \mathrm{Re}\]As we have assumed Re<5000, we can use this equation. This equation will be used in later step to solve for diameter.
03

Apply Bernoulli’s equation

In order to calculate the diameter of the pipe, we will apply Bernoulli’s equation with some assumptions. The equation is as follows:\[\frac{v^{2}}{2} + gz +\frac{p}{\rho}=\text{constant}\]Assume that the gravitational potential energy and the kinetic energy of the gas are negligible compared to the pressure energy, simplifying Bernoulli’s equation to:\[p_{1} + \frac{1}{2} \rho v_{1}^{2} + \rho g z_{1} = p_{2} + \frac{1}{2} \rho v_{2}^{2} + \rho g z_{2}\]Assuming the gas is ideal: \(p_1 = \rho R T\). Also within a pipe \(v_1 = \dot{m} / (\rho \pi D^{2}/4)\) . Since the gas is vented to outer space where \(p_2=0\), \(z_2=0\) and \(v_2=0\) , we get these equations to calculate unknowns.
04

Calculate Diameter

Substitute the equations from Step 3 and friction factor from Step 2 to derive a quadratic equation for the diameter \(D\). Solve this equation to get the value of \(D\). If the Reynolds number with this diameter is greater than 5000, it means the initial assumption was not correct. In this case, use the turbulent flow friction factor instead of laminar one and solve the equations again. Do not forget that Reynolds number changes with the change in \(D\).
05

Validate the Answer

Recalculate the Reynolds number using the obtained diameter and make sure it matches the assumed flow conditions (laminar or turbulent). If Reynolds number doesn’t match, one should go back to follow the process for the other flow conditions, iterating until you have a consistent solution.

Unlock Step-by-Step Solutions & Ace Your Exams!

  • Full Textbook Solutions

    Get detailed explanations and key concepts

  • Unlimited Al creation

    Al flashcards, explanations, exams and more...

  • Ads-free access

    To over 500 millions flashcards

  • Money-back guarantee

    We refund you if you fail your exam.

Over 30 million students worldwide already upgrade their learning with Vaia!

One App. One Place for Learning.

All the tools & learning materials you need for study success - in one app.

Get started for free

Most popular questions from this chapter

Determine the Mach number of a car moving in standard air at a speed of (a) \(25 \mathrm{mph}\) (b) \(55 \mathrm{mph},\) and (c) \(100 \mathrm{mph}\)

An airplane is flying at a flight (or local) Mach number of 0.70 at $10,000 \mathrm{m}$ in the Standard Atmosphere. Find the ground speed (a) if the air is not moving relative to the ground and (b) if the air is moving at $30 \mathrm{km} / \mathrm{hr}$ in the opposite direction from the airplane.

An aircraft cruises at a Mach number of 2.0 at an altitude of \(15 \mathrm{km} .\) Inlet air is decelerated to a Mach number of 0.4 at the engine compressor inlet. A normal shock occurs in the inlet diffuser upstream of the compressor inlet at a section where the Mach number is \(1.2 .\) For isentropic diffusion, except across the shock, and for standard atmosphere, determine the stagnation temperature and pressure of the air entering the engine compressor.

Air enters a frictionless, constant area duct with \(\mathrm{Ma}=2.5\) \(T_{0}=20^{\circ} \mathrm{C},\) and \(p_{0}=101 \mathrm{kPa}(\mathrm{abs}) .\) The gas is decelerated by heating until a normal shock occurs where the local Mach number is \(1.3 .\) Downstream of the shock, the subsonic fow is accelerated with heating until it exits with a Mach number of \(0.9 .\) Determine the static temperature and pressure, the stagnation temperature and pressure, and the fluid velocity at the duct entrance, just upstream and downstream of the normal shock, and at the duct exit. Sketch the temperature- entropy diagram for this flow.

The gas entering a rocket nozzle has a stagnation pressure of \(1500 \mathrm{kPa}\) and a stagnation temperature of \(3000^{\circ} \mathrm{C}\). The rocket is traveling in the still Standard Atmosphere at \(30,000 \mathrm{m}\). Find the throat and exit area for a flow rate of \(10 \mathrm{kg} / \mathrm{s}\). Assume \(k=1.35, R=\) \(287.0 \mathrm{N} \cdot \mathrm{m} / \mathrm{kg} \cdot \mathrm{K} .\) The gas is perfectly, expanded to the ambient pressure.

See all solutions

Recommended explanations on Physics Textbooks

View all explanations

What do you think about this solution?

We value your feedback to improve our textbook solutions.

Study anywhere. Anytime. Across all devices.

Sign-up for free