I have a video on my YouTube that goes through the process of how to set up and run a CFD problem using SU2 (here’s my video on how to download SU2).  I have the necessary files available for you to download below.  There are only two files that you need: the mesh file (.su2) and the configuration file (.cfg).  Just make sure these are both placed in the same directory, and you should be good to go.  Note that I’m using version 4 of SU2, so if you download the newest version and it won’t run properly, it’s probably because there are a couple differences between the configuration files from the old to the new versions.  The error messages are actually quite good, so it might be a good exercise for you to update your configuration file until it works.

Anyway, as promised, here are the files that should work automatically without any editing on your part.  They both need to be in the same directory, and then you just run the .cfg file using “SU2_CFD OS_Single.cfg”.

Mesh_OS_Single.su2

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OS_Single.cfg

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I have a video on my YouTube channel that computes the area ratio of the normal shock in the diverging section of a converging-diverging (CD) nozzle.  At the end of the video, I go through my MATLAB code.  Here are the files you need in order to run the code.  The main file is called CD_Nozzle_NSN.m.  The functions you will need are called ISENTROPIC_FLOW.m, NORMAL_SHOCK.m, and NS_NOZZLE.m.  You can find the isentropic flow function and normal shock function at my GitHub.  You can also just download all four files down below.

CD_Nozzle_NSN.m

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NS_Nozzle.m

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ISENTROPIC_FLOW.m

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NORMAL_SHOCK.m

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In this post, I will be explaining (and providing) some code that I use to find the pressure ratio delineations for converging-diverging (CD) nozzles.  If you are new to the subject of CD nozzles, it would be helpful to check out this video that I have made regarding CD nozzle operating states.  The math behind this blog post can be found in this video.  You can download the code used in the example by clicking on the download form below.  You will also need to download the ISENTROPIC_FLOW and NORMAL_SHOCK functions listed below, or you can get them from my GitHub repository.

CD_Nozzle_Delineations.m

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ISENTROPIC_FLOW.m

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NORMAL_SHOCK.m

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For this example, we will be assuming a nozzle area ratio of 3 () and a specific heat ratio of 1.4 ().  In the subsequent equations, there are lots of terms that include , and the location of parentheses can be sort of confusing.  What I like to do is to define some of those convenient parameters before we move on in the program.  In the code below, you can see where we define and , and below that, the convenient parameters.

% Knowns
Ae_At = 3;
g     = 1.4;

% Convenient parameters
gm1   = g-1;
gp1   = g+1;
gogm1 = g/gm1;
gm1o2 = gm1/2;
gogp1 = g/gp1;

Continue reading Converging-Diverging Nozzle Pressure Delineations→

In this post, I’ll be going through how to solve another integral, this time using trig-substitution.  As I mentioned in my u-substitution post, I’m writing this post as a reference for a future video/post about aligning torque, and I specifically needed to solve this integral.  If you would like a more neatly formatted document, you can find the attached PDF at the end of the post.  The integral we will be solving can be seen below.

(1)  

Continue reading Integral – Trig Substitution→

In this post, I’ll be going through how to solve an integral using u-substitution.  This is not an exhaustive document about all the tips and tricks for u-substitution.  I’m simply writing this post as a reference for a future video/post about aligning torque, and I specifically needed to solve this integral.  If you would like a more neatly formatted document, you can find the attached PDF at the end of the post.  The integral we will be solving can be seen below.

(1)  

Continue reading Integral – U-Substitution→

In this post, we will be going through the derivation of the turbofan thrust equation.  More specifically, this is the thrust equation derivation for a double inlet/double outlet engine.  I usually use the WordPress Latex math for Semal Musli improves vitality of your reproductive system and strengthens your body to perform better in bed. pdxcommercial.com cialis 10 mg Expecting women also face the problem of semen leakage, infections and allergies. super cheap viagra This is because you will be able to take cialis no prescription mastercard advantage of it from the beginning. Working of generika cialis 20mg jelly : Erectile Dysfunction (ED) than men who make love less often. my posts that need equations, but this particular derivation needed more packages than were available, so I have uploaded a PDF for you to download that includes the whole derivation.  Just click on the link below.

Thrust_Equation_Turbofan.pdf

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In this post, we will be going through the derivation of the turbojet thrust equation.  More specifically, this is the thrust equation derivation for a single inlet/single outlet engine.  I usually use the WordPress Latex math for my posts that need equations, but this particular derivation needed more packages than were available, so I have uploaded a PDF for you to download that includes the whole derivation.  Just click on the link below.

Thrust_Equation_Turbojet.pdf

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If you would like to follow along in video form, here is my YouTube video on this topic that goes through the same derivation (and is color coded!).

In this post, we will derive the differential form of the quasi-1D mass conservation equation.  We will be starting from the result of the quasi-1D mass conservation derivation that will be discussed in a different post (and will be linked to here when it becomes available).  The quasi-1D mass conservation equation can be written as the following.

(1)  

Now we need to convert this to differential form.  That is, we want this equation in terms of changes in the variables (, , ).  There are a few different methods we can use here, and I’ll go through each of them for completeness.  I will be using the abbreviations LHS and RHS for left-hand side and right-hand side, respectively.

Continue reading Differential Form: Quasi-1D Mass Conservation→

In this post, I’m going to continue the discussion I started in my Volume Integrals post, but we will move on to the discussion of double, or surface, integrals.  The double and triple integrals show up in every term of the conservation equations when couching them in integral form, so they are extremely relevant in any discussion of fluids or thermal studies.  I dealt with triple integrals first because they are intuitively easier to understand.  The trouble with double integrals arises because we are dealing with stuff that flows through the control surface (CS), as opposed to trying to account for something just sitting inside of a control volume (CV).  The main difficulty in the understanding of the double integral terms results from the elegantly inherent way that we account for whether stuff is coming into the CV, or going out of the CV.

Continue reading Surface (Double) Integrals→