Thanks you very much for the tutorial , MOSTLY for tip at 10.01 . I am doing an other symmetrical model ( 3 D airfoil into a cube fluid domain ) . I have found a big problem ! Fluent doesn't accept my meshing ! Due to this video , i have realized that i must deactivate contact region , If not Fluent will diverge ! Thanks you again
@@ansys_cfd Can you help me here, I'm doing CFD analysis of a UAV in ANSYS fluent and I have a problem with meshing. Important an IGES, STL, SAT, parasolid files into meshing takes too long and then finally gives an error. When I modelled a part of the UAV in design modeller the meshing took less than 3 minutes. What could be wrong?
Hello, Thanks for this video. I am studying the flow around a 3D wing and would like help with the reference values to be specified in Ansys Fluent. I know the area is the top surface of the wing, the length is that of the chord. But my problem is that the chord is not constant all the way down the wing (the chord at the root is bigger than the salmon one). How can I specify the chord in this case, please ?
Hello mates, I want to ask something about analysis which are made on airfoils. What are the benefits of two-dimensional analysis for airfoils, As far as I know, three-dimensional analyses are not usually chosen by people who do experiments on airfoils, why are we choosing two-dimensional over the three-dimensional analysis?
Thanks for tutorial, i have 2 questions. Why we need the rectangular behind the airfoil? Can we don't suppress (in the begining mesh 4:41 ) for thinking this part is like a fuselage?
same question . I have done the same symmetrical model without the rectangle . Surprise ! I don't have get any result after calculation . I don't understand why
@@Veyselahmet97 Thanks I have checked the problem : first i have forgotten to use bolean function , second , i did not precised to Fluent reference zone ( airfoil). I have fixed the two problem , my model works perfectly. Now as a response to your question : the rectangle is used to make a refined meshing zone around the airfoil.
@@Veyselahmet97 i advice you to use geometry with rectangle. This method allows you more precise solution around airfoil area because mesh will be more reffined
Hi Freind . Can we instead of suppressing contacts regions at 9.52 ( in the order to avoid overlapping contacts) , insert manually contacts and use later interface option in Fluent ? I am asking the question because contact regions are important to make our mesh conformal . If we suppress it , mesh is no more conformal. Thanks you for response and for your remarks about my question. Have a nice day
Hi friend; These contacts regions appear because I created some bodies in DesignModeler for use Body of Influence, but these contacts don't use for the simulation in this case. You can create only the default domain and generate a new mesh without other bodies, so the contacts don't appear. Best regards
Hi! I'm trying to do the same as you but with a different model. I'm working on Ansys Workbench R2 2019 and I have just finished to mesh the model. But when I open setup I can't go further because they said that they only accept models with a maximum of 512 000 cells. What do I have to do ? Thanks you so much !
@@ansys_cfd Sorry, I have just another question : do you know if it is possible to change the fluid direction in Fluent? For exemple if we want to have a fluid with a 20degrees incidence angle? thank you!
@@moorlandstotilas1115 You can also select the option of insert velocity by components (something like that) you will have to calculate the components and then input them. But, it is also important to know, drag and lift forces need to be measure in parallel and perpendicular respectively to the incoming free flow. Meaning, 12:37 at that moment you also need to input the correct force vector for each coefficient.
Hi ninja, did everything as you did. In 2nd edge sizing its taking hella lot of time. I only changed preference from linear to quadratic can it be related
Please help me !! I am conducting a study of the effects of vortex generators on airfoil. What is the additional meshing steps that I need to do after I add several vortex generators on the airfoil ? The meshing steps really difficult for me.
13:18 , Can you help me , after initializations programm shows me Warning : Unassigned interface zone detected for interface 10 , How can I solve this problem ?
Excuse me, I want to ask what is the difference between Ansys R1 and Ansys R2 ? is it a different function? or how ? I'm new to this application and want to install it. I want to learn more deeply, I hope to get a response, thanks
Heyy I would like to know whether I can do the same thing...but with a very small bird wing (one half of it) This wing is already designed in a cad software and imported Would it be possible to follow your tutorial for the same ?m
Hi Why did you make domain by using extrusion operation on rectangle instead using in built option "enclosure" ?? Is there is any difference or any advantage of this method ??
Hello great tutorial. I have one question though. I want to set a propeller before the wing to see how it sucks the air (basiclly i want to model the start of the plane) and I'm not sure what type of Cell zone conditions and boundary condiotion to use. I made a domain for the propeller and substract solid form that domain( and followed yours tutorial for the wing) and then in Solutions I've picked cell zone condition for that domain as a Frame motion and set the rpm , then i set the boundary condition for inlet and outlet at 0 preasure ( the rest was like the tutorial ) But in the end it gave me no results and I dont know what to do right now :P hope someone could tell me what i need to fix :D
I have followed all the mentioned steps for naca 25112 at a 13 degree angle, and I am not getting any decent drag accuracy. I have calculated also the y plus and ensured that my inflation layers grow rate helps it to grow smoothly up to surrounding tetrahedral mesh. what is there else to be done? Thanks in advance.
Hi friend; Please review this tutorial: ruclips.net/video/V_ozqKflSx8/видео.html There is a correct setting about reference values (Drag coeffcient) Best regards
Wondering why the velocity is so low (12m/s)? Is that significant, or can the simulation be changed to a higher value to simulate specific circumstances?
i am currently using version 2020 R2 of ANSYS, whenever I open the geometry spaceclaim i do not get a "tree outline" with the different axis' on my left side window, the only thing that comes up "Design 1" therefore I have no idea how to import my airfoil data from here. Is there anywhere I can default to the tree outline option or is it because I am using a newer version of the software? PLEASE HELP thank you
hi, I have a question about the video. I see that the mesh before running the simulation is tetrahedral mesh. But the mesh showed in the post processing stage is the polyhedral mesh. Why is this happening?
Hello! Thanks for the tutorial! I have a problem after adding the inflation as in 6:40 did. After clicking on Generate Mesh, my mesh switched from quadrilateral to triangles, but there was no prism layer. I did exactly the same previous steps as you did. Do you know how to resolve this? Thanks.
@@ansys_cfd Hi, I also want to do 2D simulation, so how can I adjust the element size in the z-direction? I extruded to 0.1m in z-direction. I want to limit the number of cells in z-direction to 1. Thanks!
Hey, how do you know what numbers to use, for example the thickness, element size and other? If I experiment with other airfoils I will probably have to use other numbers right ?
Hi friend; Yes if you change the velocities values you need to change some values, for this is necessary to do a sensibility analysis of the mesh. Best regards
The way you have created walls on either side of airfoil tip- we will lose the flow physics due to tip vortex. Any particular reasons walls were flushed to sides of airfoil?
Hi friend; The purpose was to obtain the values of the lift and drag coefficient, if we change the walls these coefficients will change, what has been done in this simulation is to represent a real laboratory case to obtain aerodynamic coefficients. Regards
Hola Raul, Hablas español? no entiendo muy bien tu consulta. Si tienes algún problema con el volumen de control debes verificar que sea totalmente solido y no una cascara. Saludos
sir can you please tell me how to change the orientation of the task page, and window position in FLUENT. I have tired to find solution for it online but could not. The project window is below and it is too small as compared to console and task page.
Hola, ninja! en el minuto 3:45 creas un rectángulo, pero no especificas las dimensiones horizontales. Es un aproximado o cual es la razón de que no se especifica? Gracias y saludos!
Hi friend; I did this simulation in 3D because several subscribers requested it, however, if you prefer a 2D simulation please visit this link: cfd.ninja/tutorials/fluent-tutorials/ Here you can find several tutorials Regards
There is an error called, "The specified defeaturing tolerance was found to be larger than a specified size. The elements on one or more edges may be defeatured out." when i try to put body of influence. which cause my mesh is not fine around backside of the air foil. do you have any idea to solve that problem?
Man, click on mesh and search: Sizing -> Mesh Defeaturing Click in the box and select "no" But if you apply a reduction in Element Size of the global mesh, looking at the value showed in Defeature Size you can make it too, all the elements cannot be higher than this global defeaturing.
Hi there! im using the ANSYS 2020 version and following this video. Everything was smooth up till the setup It says that "An error occurred in FLUENT while applying case and setting information." Thanks in advance!
Hey first go to airfoiltools.com search for any profile that u want and copy the cordinate and paste it on a text file then copy them to excel and initialize the first colone with 1 all of them then the next colone is try to sort all ur coordinations from 1 - to 30 or maybe 40 or i dont know them place ur coordinations and the last colone is to initialize them with zeroos 0 then copy everything and past it on a new text file then open it in Ansys fluent and if u need help contact me on my email ali19chakir@gmail.com
@@aakashsadar9564 Hi friend; Here a video about compressible flow maybe can help: ruclips.net/video/YfsPxn9_3fA/видео.html Here a calculator for Y+: www.cfd-online.com/Tools/yplus.php Best regards
@@ansys_cfd I am following all the steps in your suggested video just changing the viscous model to k-w SST for 3D. and i am getting error in operating pressure and outlet gauge pressure. the error is - "apply positive non zero pressure boundary conditions when using the ideal gas law for density" how to fix this please reply
Hey, I hope you are till reading the comments of this videos as you're my only hope to solution of my problem to which no one seems to know the answer. When I import the txt document of the coordinates(any of them), ansys shows that it's not able to "read the coordinate file". I have no idea why this does not work. My ansys version is 18.1 Thank You and Regards.
Hi friend, In the description you can find the link (cfd.ninja website, the download link is on the video). You can download the points to create the NACA airfoil, you must watch the tutorial so you can generate the mesh. this link has no password. Regards
@@ansys_cfd Hello. I just did , when I try to open the Rar file it sais "The archive file is either Unknown format or damaged" ... what do I do? Would you mind sending the file unzipped to my email or something... would mean a lot :) madric6111@yahoo.com
@@ansys_cfd I am having similar situation. It is showing error cant locate the coordinate point. Could you please help send the file also adekoladekola@gmail.com. Thank you I anticipate your response
Hi friend; Please try to download again the file. In the file are the NACA body (*.step) and the points. cfd.ninja/ansys-fluent/ansys-fluent-airfoil-3d-naca-4412/ Regards
Yeah makes sense now, I followed exactly your steps and apparently it creates problem in Fluent due to the limitations in the number of cells to operate with in the Student version
Wow, this information is ver useful for my bachelor's degree's Project. Thank you so much. ✌🏼🎉
this video is quit useful ... it make a rapid punch for Ansys fluent Learning
thank you so much for sharing this knowledge! it's really generous of you
You're welcome friend. Best regards
@@ansys_cfd hi can you send me another link to download file
Să-ți dea Dumnezeu sănătate!
Mulțumesc foarte mult
I was looking a lot for a good ANSYS tutorial and I found it here! Excellent CFD Ninja
Plotting airfoil without closing trailing edge and linking them again with a line made this simulation look harder...lol😂
Yes is possible, you can even round the trailing edge and get all the data around the airfoil.
You’re so great bro, thanks
Thank you friend.
Best Regards
gud miusic
nice one sir well done 👍👍👌
Thanks friend.
Best Regards
Thanks you very much for the tutorial , MOSTLY for tip at 10.01 . I am doing an other symmetrical model ( 3 D airfoil into a cube fluid domain ) . I have found a big problem ! Fluent doesn't accept my meshing ! Due to this video , i have realized that i must deactivate contact region , If not Fluent will diverge ! Thanks you again
Did you try cfx?
@@Abduldoctor not yet , i am using actually Fluent , but i will resolve the same problem with cfx AND COMPARE with Fluent
You're welcome friend.
Best regards
You are an inspiration to me. Thanks!!!
Thank you!
@@ansys_cfd Can you help me here, I'm doing CFD analysis of a UAV in ANSYS fluent and I have a problem with meshing.
Important an IGES, STL, SAT, parasolid files into meshing takes too long and then finally gives an error. When I modelled a part of the UAV in design modeller the meshing took less than 3 minutes.
What could be wrong?
Hello,
Thanks for this video. I am studying the flow around a 3D wing and would like help with the reference values to be specified in Ansys Fluent. I know the area is the top surface of the wing, the length is that of the chord. But my problem is that the chord is not constant all the way down the wing (the chord at the root is bigger than the salmon one). How can I specify the chord in this case, please ?
Really useful, thanks!
Thanks friend
Hey there comes an error when importing the geometry to design modler
The file i downloaded from the link can not be used in ansys cause of the error reading coordinates file. Could you please help me regarding this
Hello! (10:43) Why you change mesh to the Polyhedra? it's better for solving?
Hi, it is faster
Thank you.
You're welcome friend
Hello mates, I want to ask something about analysis which are made on airfoils. What are the benefits of two-dimensional analysis for airfoils, As far as I know, three-dimensional analyses are not usually chosen by people who do experiments on airfoils, why are we choosing two-dimensional over the three-dimensional analysis?
Danke Schön
thank you so much
You're welcome friend. Best Regards
The best! Thank you so much
Can you please make a tutorial on meshing the wing with its winglet? Thanks for this video it was helpful.
Hi friend;
I will try in the future.
Thanks!
10:49
You clicked convert to polyhedral
But you said it will be converted to hexahedral
this is really helping my final project. I have a question tho, do you have any reference for how big the fluid domain must be?
Good question, it should be big enough so that the pressures around it don't affect the results. This mainly depends on the Reynolds number
I couldn't import coordinates to Ansys. I am taking reading coordinates file error. How can I fix this problem?
thanks! it's useful for me.
You're welcome friend
Best regards
what is the difference if i don't use that body of influence mesh? i mean, i will just make the mesh element size smaller
Can you please make a tutorial on analysis of vortex generator on an airfoil?
Hi friend;
Do you have any Paper about that topic? It is necessary to obtain data.
Regards
@@ansys_cfd Experimental Investigation of Conformal Vortex Generators via
Wake Survey by KC Nicholas
doi.org/10.2514/6.2019-0578
Thanks for tutorial, i have 2 questions.
Why we need the rectangular behind the airfoil?
Can we don't suppress (in the begining mesh 4:41 ) for thinking this part is like a fuselage?
same question . I have done the same symmetrical model without the rectangle . Surprise ! I don't have get any result after calculation . I don't understand why
@@manelsouguir8126 i did without the rectangle and i got results, when i compared it with experimental data, i had close results.
@@Veyselahmet97 Thanks I have checked the problem : first i have forgotten to use bolean function , second , i did not precised to Fluent reference zone ( airfoil). I have fixed the two problem , my model works perfectly.
Now as a response to your question : the rectangle is used to make a refined meshing zone around the airfoil.
@@manelsouguir8126 Thanks, i want to aeroacoustic analysis with receivers (mics), what do you think i need to use the rectangle or dont need?
@@Veyselahmet97 i advice you to use geometry with rectangle. This method allows you more precise solution around airfoil area because mesh will be more reffined
Hi Freind . Can we instead of suppressing contacts regions at 9.52 ( in the order to avoid overlapping contacts) , insert manually contacts and use later interface option in Fluent ?
I am asking the question because contact regions are important to make our mesh conformal . If we suppress it , mesh is no more conformal.
Thanks you for response and for your remarks about my question.
Have a nice day
Hi friend;
These contacts regions appear because I created some bodies in DesignModeler for use Body of Influence, but these contacts don't use for the simulation in this case. You can create only the default domain and generate a new mesh without other bodies, so the contacts don't appear.
Best regards
@@ansys_cfd Ok Thanks you very much
thank you sooooo much :)
You´re welcome friend. Soon more tutorials
Best regards
Can you please make a video on Analysis of aerofoil (NACA0012) with gurney flap in CFD
Hi! I'm trying to do the same as you but with a different model. I'm working on Ansys Workbench R2 2019 and I have just finished to mesh the model. But when I open setup I can't go further because they said that they only accept models with a maximum of 512 000 cells. What do I have to do ? Thanks you so much !
Hi friend, I think that you have the academic license, you need commercial or research license. Regards
@@ansys_cfd okay thanks !
@@ansys_cfd Sorry, I have just another question : do you know if it is possible to change the fluid direction in Fluent? For exemple if we want to have a fluid with a 20degrees incidence angle? thank you!
@@moorlandstotilas1115 you can change your angle of attack by rotating the geometry. See CFD Ninja tutorial on Naca0012
@@moorlandstotilas1115 You can also select the option of insert velocity by components (something like that) you will have to calculate the components and then input them. But, it is also important to know, drag and lift forces need to be measure in parallel and perpendicular respectively to the incoming free flow. Meaning, 12:37 at that moment you also need to input the correct force vector for each coefficient.
Hi ninja, did everything as you did. In 2nd edge sizing its taking hella lot of time. I only changed preference from linear to quadratic can it be related
Hello I need help to do sediment erosion analysis on naca 4412 francis turbine guide vane.can you please create video for that
Please help me !! I am conducting a study of the effects of vortex generators on airfoil. What is the additional meshing steps that I need to do after I add several vortex generators on the airfoil ? The meshing steps really difficult for me.
it shows error when i try to open the NACA airfoil file in design modeler. it says "Invalid Group/Id found in Coordinates file".
hey could please make a video on flutter analysis using fluent?
I love u!
13:18 , Can you help me , after initializations programm shows me Warning : Unassigned interface zone detected for interface 10 , How can I solve this problem ?
Excuse me, I want to ask what is the difference between Ansys R1 and Ansys R2 ? is it a different function? or how ? I'm new to this application and want to install it. I want to learn more deeply, I hope to get a response, thanks
Heyy I would like to know whether I can do the same thing...but with a very small bird wing (one half of it)
This wing is already designed in a cad software and imported
Would it be possible to follow your tutorial for the same ?m
Hi
Why did you make domain by using extrusion operation on rectangle instead using in built option "enclosure" ?? Is there is any difference or any advantage of this method ??
You can use enclosure too, it is the same. The important is that the domain must be identical to Real model.
Hello great tutorial. I have one question though. I want to set a propeller before the wing to see how it sucks the air (basiclly i want to model the start of the plane) and I'm not sure what type of Cell zone conditions and boundary condiotion to use. I made a domain for the propeller and substract solid form that domain( and followed yours tutorial for the wing) and then in Solutions I've picked cell zone condition for that domain as a Frame motion and set the rpm , then i set the boundary condition for inlet and outlet at 0 preasure ( the rest was like the tutorial ) But in the end it gave me no results and I dont know what to do right now :P hope someone could tell me what i need to fix :D
Can you put video for enclosure tutorial
I have followed all the mentioned steps for naca 25112 at a 13 degree angle, and I am not getting any decent drag accuracy. I have calculated also the y plus and ensured that my inflation layers grow rate helps it to grow smoothly up to surrounding tetrahedral mesh. what is there else to be done? Thanks in advance.
Hi friend;
Please review this tutorial: ruclips.net/video/V_ozqKflSx8/видео.html
There is a correct setting about reference values (Drag coeffcient)
Best regards
Wondering why the velocity is so low (12m/s)? Is that significant, or can the simulation be changed to a higher value to simulate specific circumstances?
For higher speeds you must know if the fluid will have a compressible behavior or not, you must also calculate the Y + and modify the mesh
@@ansys_cfd great, thankyou!
i am currently using version 2020 R2 of ANSYS, whenever I open the geometry spaceclaim i do not get a "tree outline" with the different axis' on my left side window, the only thing that comes up "Design 1" therefore I have no idea how to import my airfoil data from here. Is there anywhere I can default to the tree outline option or is it because I am using a newer version of the software? PLEASE HELP thank you
hi,
I have a question about the video.
I see that the mesh before running the simulation is tetrahedral mesh.
But the mesh showed in the post processing stage is the polyhedral mesh.
Why is this happening?
Hi friend, You need to update the mesh. Hide the mesh and unhide the mesh. Regards
thaksss pal
hi, why didn't you apply a boolean also to the second box (the smaller one)?
There are several ways to find the right results. You can apply boolean and test. Regards
Hello! Thanks for the tutorial! I have a problem after adding the inflation as in 6:40 did. After clicking on Generate Mesh, my mesh switched from quadrilateral to triangles, but there was no prism layer. I did exactly the same previous steps as you did. Do you know how to resolve this? Thanks.
Hi friend;
Update the mesh in Ansys fluent, , click on display mesh unselect the surfaces, Apply and then select the surfaces and Apply. Regards
@@ansys_cfd Hi, I also want to do 2D simulation, so how can I adjust the element size in the z-direction? I extruded to 0.1m in z-direction. I want to limit the number of cells in z-direction to 1. Thanks!
@@yukunsun2110 Hi friend; Here I share a tutorial about 2d Simulation for NACA Airfoil:
cfd.ninja/ansys-fluent-naca-airfoil-4412/
Best regards
Hey, how do you know what numbers to use, for example the thickness, element size and other? If I experiment with other airfoils I will probably have to use other numbers right ?
close to these numbers..
Hi friend;
Yes if you change the velocities values you need to change some values, for this is necessary to do a sensibility analysis of the mesh.
Best regards
The way you have created walls on either side of airfoil tip- we will lose the flow physics due to tip vortex. Any particular reasons walls were flushed to sides of airfoil?
Hi friend;
The purpose was to obtain the values of the lift and drag coefficient, if we change the walls these coefficients will change, what has been done in this simulation is to represent a real laboratory case to obtain aerodynamic coefficients.
Regards
My big rectangle is hollow in the back when meshing , how can i solve, im using Citrix , maybe has low processing power
Hola Raul,
Hablas español? no entiendo muy bien tu consulta. Si tienes algún problema con el volumen de control debes verificar que sea totalmente solido y no una cascara.
Saludos
Hi, may I know where can I look for the lift and drag coefficient results?
Hi friend,
Here a tutorial about Lift and Drag coeffcients.
ruclips.net/video/V_ozqKflSx8/видео.html
Regards
how can ı set the AoA for parameter ?
sir can you please tell me how to change the orientation of the task page, and window position in FLUENT. I have tired to find solution for it online but could not. The project window is below and it is too small as compared to console and task page.
Hi friend,
Can you send an email with an image to support@cfd.ninja?
Best regards
bro 4:47 in outline block, I am not getting the materials in geometry. what can i do ?
How did you decide that the width of the fin and fluid domain should be the same?
Real experimento in Lab
Hola, ninja! en el minuto 3:45 creas un rectángulo, pero no especificas las dimensiones horizontales. Es un aproximado o cual es la razón de que no se especifica? Gracias y saludos!
Bro it's showing fatal error......thrust failed.....pls help🙏
Can u make a video for NACA 0012 AIRFOIL For helicopter rotor blade in fluent
Maybe in the future when I have the geometry and time.
Best regards
can you enlight us about why did you prefer to analyse this in 3d
Hi friend;
I did this simulation in 3D because several subscribers requested it, however, if you prefer a 2D simulation please visit this link:
cfd.ninja/tutorials/fluent-tutorials/
Here you can find several tutorials
Regards
Please can you help me how I get Lift coefficients and drag coefficients for this 3d airfoil
Hi friend;
Please check this tutorial: ruclips.net/video/RQip8bElJEc/видео.html
You should setting Reference Values
Regards
Sir can you post a tutorial video of 2d airfoil with leading edge rotating cylinder. I have searched the whole internet, but can't find one.
Thanks for the idea
@@ansys_cfd Thank You. The tutorial will be very helpful for me.
I couldn't get the file
There is an error called, "The specified defeaturing tolerance was found to be larger than a specified size. The elements on one or more edges may be defeatured out." when i try to put body of influence. which cause my mesh is not fine around backside of the air foil. do you have any idea to solve that problem?
Man, click on mesh and search: Sizing -> Mesh Defeaturing
Click in the box and select "no"
But if you apply a reduction in Element Size of the global mesh, looking at the value showed in Defeature Size you can make it too, all the elements cannot be higher than this global defeaturing.
Hello !
How can we do if the fluent simulation doesn’t converge ? ( for incline airfoil : 10 degrees)
Hi, Several things can be done. the most recommended are to improve the mesh or change the numerical scheme
Hi there! im using the ANSYS 2020 version and following this video. Everything was smooth up till the setup
It says that "An error occurred in FLUENT while applying case and setting information." Thanks in advance!
Hi;
Are you using a commercial or research license?
Regards
@@ansys_cfd hi! I am using student version..... sorry I am new to this...
@@tanamelia3066 For this tutorial you need the full version, Academic version is limit.
Best regards
@@ansys_cfd is there a way to edit the mesh such that it is within the version limit?
when i want to make the inflation, i dont see 2 internal surface. only have 1 surface. can u help me?
Hi, What minute please?
Hi bro, could you help me with the low velocity problem (1.8 m/s), please?
Hi friend;
You try to do the same process and change the velocity only.
Regards
I need to know how the profile coordinates are imported
Hey first go to airfoiltools.com search for any profile that u want and copy the cordinate and paste it on a text file then copy them to excel and initialize the first colone with 1 all of them then the next colone is try to sort all ur coordinations from 1 - to 30 or maybe 40 or i dont know them place ur coordinations and the last colone is to initialize them with zeroos 0 then copy everything and past it on a new text file then open it in Ansys fluent and if u need help contact me on my email ali19chakir@gmail.com
what if the speed is over Mach = 1. Is there any different setting or we just increase the speed to that value?
You need to calculate Y+
@@ansys_cfd sir, is there any way i can contact you personally? I have some doubt in my project.
@@ansys_cfd can you suggest your any video in which you calculate turblent flow on k-w sst for mach>1? Please
@@aakashsadar9564 Hi friend;
Here a video about compressible flow maybe can help: ruclips.net/video/YfsPxn9_3fA/видео.html
Here a calculator for Y+: www.cfd-online.com/Tools/yplus.php
Best regards
@@ansys_cfd I am following all the steps in your suggested video just changing the viscous model to k-w SST for 3D. and i am getting error in operating pressure and outlet gauge pressure. the error is - "apply positive non zero pressure boundary conditions when using the ideal gas law for density" how to fix this please reply
Hey, I hope you are till reading the comments of this videos as you're my only hope to solution of my problem to which no one seems to know the answer.
When I import the txt document of the coordinates(any of them), ansys shows that it's not able to "read the coordinate file". I have no idea why this does not work. My ansys version is 18.1
Thank You and Regards.
It imports fine in solidworks as well and i make the txt document in excel sheets
Friend
Are you trying to open the txt of this tutorial?
Regards
Hi! Why the file I download from your website is unavailable to export? It shows it's a STP file
Hi friend,
That is the only file that I am sharing, it is the geometry, which is enough for you to develop the tutorial.
Regards
Aren't you all getting an option to input a password to download the mesh file from the link provided?
Hi friend,
In the description you can find the link (cfd.ninja website, the download link is on the video). You can download the points to create the NACA airfoil, you must watch the tutorial so you can generate the mesh. this link has no password.
Regards
im running a student edition and it says theres too many cells to process :/
Hi friend;
You need research or a commercial version for this simulation.
Regards
Can you please provide the coordinates file as tje file available on the above-mentioned link is not working. Thanks in advance
Hi friend;
In this website you should the file: cfd.ninja/ansys-fluent/ansys-fluent-airfoil-3d-naca-4412/
Regards
@@ansys_cfd Thanks
is this time dependent or steady state?
Hi, This is steady.
Regards
can the small box be any size?
Hi friend;
It must be large enough not to affect pressure gradients.
Regards
el archivo .txt no esta para descargar, solo esta el archivo .stp
what is the reason to apply inflation ?
Hi friend;
Refine the mesh in the wall of the airfoil.
Regards
In the boundary layer there is a big pressure and velocity gradient due viscosity effects. You use the inflation to capture better this gradient.
Hello I'm having a problem with the NACA file when I download,it sais it's corrupt for some reason....can you please help..
Hi friend;
I downloaded I the file works.
Can you try again please?
Regards
@@ansys_cfd
Hello.
I just did , when I try to open the Rar file it sais "The archive file is either Unknown format or damaged" ... what do I do? Would you mind sending the file unzipped to my email or something... would mean a lot :) madric6111@yahoo.com
Hi @@stefanalhayess1299 the file is a *.stp (CAD file) you must open it with DesignModeler or SpaceClaim. I will send the file.
Regards
@@ansys_cfd I meant when I download the file it gives me an error. Thank yo soo much you're a life saver
@@ansys_cfd I am having similar situation. It is showing error cant locate the coordinate point. Could you please help send the file also adekoladekola@gmail.com. Thank you I anticipate your response
hello, im trying to find the file in that website but I can't found it. do u mind to share it
Hi friend,
The file is works, please try again. The file are the points (text).
Regards
which version of ansys did u use?
Hi,
This simulación was made with Ansys 19
Regards
i download the file but it does not exist your DM file, it has STP file
You can importa step file in DM
@@ansys_cfd i tried your step file, but encountered 'Error reading Coordinates File'
So, you import the points only as show the video.
@@ansys_cfd I suffered the same problem
PRINT TO SMALL OR NOT CLEAR
PRINT TO BIG OR CLEAR
Hello, I want to ask if the downloaded file is stp file
correct, i'm confused when importing the file
Hi friend;
Please try to download again the file. In the file are the NACA body (*.step) and the points.
cfd.ninja/ansys-fluent/ansys-fluent-airfoil-3d-naca-4412/
Regards
I like the video but I think you are too fast, can you slow down a bit please? It's hard to catch up sometimes
Dear friend, in the setting bar of the video there is the option to modify the speed, you can reduce it so that the video is slower.
Okay thank you very much. Btw, are you using the student version?
@@IrfanKhan-ds6jv This tutorial using commercial version. Regards
Yeah makes sense now, I followed exactly your steps and apparently it creates problem in Fluent due to the limitations in the number of cells to operate with in the Student version
we know youre smart dont need to show that fast
Also, I know that You are Smart, you can use pause button.