If your airspeed is 400 m/s, you are in the supersonic regime, means pressure-solver(see edit), energy eqn, way more iterations! This is how NOT to use cfd! you get pretty colors as a result, but none of them are remotely correct! EDIT: Just getting notices of this comment from 3 years ago, but obviously I meant to say that you should be using the density-solver for supersonic flow, while you instead used the pressure-based solver, and without energy equations or changing to an ideal gas/compressible fluid. Though I should note (for those getting upset by my mistake 3 years ago..), the pressure solver can in fact be used for compressible cases (the solver was updated to include compressibility a long time ago), and I know people that have found better convergence with it in special situations, though I would say that is more the exception than the rule. (But not having energy eqn or changing the fluid material is just outright wrong, and reminds me wayy too much of second-year undergrads who think they can solve any CFD problem cause they managed to open Ansys once..) Also the fluid domain is wayyy to small (yes, you can get away with smaller domains for supersonic, but nearly this level! I'd suggest the domain be *at very least* 2x your wing span, likely more)
The pressure-solver must be applied above 0.3 Mach not only for sonic and supersonic speeds, because at this point fluid turns compressible and it will be necessary energy eqn to obtain values
One suggestion, you could have simplified the analysis by cropping the volume to the half since the aircraft is symetric, this way you user less resources and the solution is faster
Hi admin! Thank you very much for this helpful tutorial. But, i clicked on the link to download the model,then system said: request the owner of this file. Then a message for access permission was sent to you. When could you send this model to me, please?
Hello, thanks for making such a good tutorial! May I know how can I show the wire frame in yellow that you had at 3'17''? My Fluid Flow does not show that although the simulation can be continued.
Hi Guys! I clicked on the link to get the f16 model. But, no one responded to my apply. How can i find this model and download solidworks file of it. Please, help me
please someone help me .. i want to set the pression and temperature value beside the speed of aircraft fly at 1000 meter.. which means pression 0.9 bar and temperature 8.5 °C how I can set it
Hi! Thanks for making such a nice tutorial. But when I click Edit under Setup after I finished setting the Geometry and Mesh, I will have load file: file not found. May I know how can I solve this problem?
Merhaba Arkadaşlar! Siz modele nasıl ulaştınız? Verdiği linke girince "dosya sahibinden erişim izni iste" dedi sistem. İstedim. "Mesajınız alındı" dedi. Sizin mailinize kaç gün sonra modeli gönderdi admin?
Helloo...I need help with a flow simulation for my final year project...i followed your video and tried doing it myself but i am having some issues after the meshing process. Could you please help me out??
Hi this was a really nice tutorial. But I am having difficulty with the results. I get blue streamlines of zero velocity. I tried to follow at the steps. Can you please help me pinpoint my mistake or if i missed something. THanks
Aerospace Technologies thank you very much for the offer. I'm wondering how to model the aircraft better. your model doesn't seem to be really accurate but gives a great idea of how to go about it. can you please some light on the modeling aspect. Regards
Bad job man. Work on it again. No summetry, no subtraction of the solid body, too small enclosure, not taking into account that you are on the supersonic flow region. Horrible. Sorry if I am harsh, but that's it.
If your airspeed is 400 m/s, you are in the supersonic regime, means pressure-solver(see edit), energy eqn, way more iterations!
This is how NOT to use cfd! you get pretty colors as a result, but none of them are remotely correct!
EDIT: Just getting notices of this comment from 3 years ago, but obviously I meant to say that you should be using the density-solver for supersonic flow, while you instead used the pressure-based solver, and without energy equations or changing to an ideal gas/compressible fluid.
Though I should note (for those getting upset by my mistake 3 years ago..), the pressure solver can in fact be used for compressible cases (the solver was updated to include compressibility a long time ago), and I know people that have found better convergence with it in special situations, though I would say that is more the exception than the rule. (But not having energy eqn or changing the fluid material is just outright wrong, and reminds me wayy too much of second-year undergrads who think they can solve any CFD problem cause they managed to open Ansys once..)
Also the fluid domain is wayyy to small (yes, you can get away with smaller domains for supersonic, but nearly this level! I'd suggest the domain be *at very least* 2x your wing span, likely more)
Exactly, the velocity changes caused by shockwaves are nowhere to be seen, shockwaves are the most important factors in supersonic flight
exactly my point
The pressure-solver must be applied above 0.3 Mach not only for sonic and supersonic speeds, because at this point fluid turns compressible and it will be necessary energy eqn to obtain values
This is so-called "Garbage-In, Garbage-Out”！
One suggestion, you could have simplified the analysis by cropping the volume to the half since the aircraft is symetric, this way you user less resources and the solution is faster
Why is the solid aircraft body not subtracted from the domain and the domain has to be 10 x bigger.
Nice beginning, good luck!
Same quality of CFD as yours FEA.
Sir iam a mechanical Engineering final year student, can I please know a source or a way learn to actually design the aircraft model.
Thank you!
thanks for share!
Hi admin! Thank you very much for this helpful tutorial. But, i clicked on the link to download the model,then system said: request the owner of this file. Then a message for access permission was sent to you. When could you send this model to me, please?
update failed for mesh components.... why this error prompts for me ?
Can u give an example on aircraft water landing simulations?
Hello, thanks for making such a good tutorial! May I know how can I show the wire frame in yellow that you had at 3'17''? My Fluid Flow does not show that although the simulation can be continued.
Hi there, the model cannot be downloaded. Pls kindly update the link.
there's a problem with your model. Some parts of it aren't connected well and is showing error in meshing
Should I add materials for aeroplane? Would you please tell me
final answer is 1004 m s-1, where have i gone wrong?
i cant see my model in the solution window , only the enclosure is seen
Hi Guys!
I clicked on the link to get the f16 model. But, no one responded to my apply. How can i find this model and download solidworks file of it. Please, help me
please someone help me ..
i want to set the pression and temperature value beside the speed of aircraft
fly at 1000 meter.. which means
pression 0.9 bar and temperature 8.5 °C
how I can set it
there are problem in meshing. in the aircraft are showing one error.
Hi! Thanks for making such a nice tutorial. But when I click Edit under Setup after I finished setting the Geometry and Mesh, I will have load file: file not found. May I know how can I solve this problem?
Hi, I have solved this problem by deleting the file in C Disk which could not be found. Thanks!
Thanks
От умора)
can you teach how to get skewness below than 0.9 for an aircraft
Could you do it with Ansys CFX as well? I don't understand the difference.
Will this work better in V19?
Ansys 17.1'de mesh oluştururken kokpit camı ve çevresinde hatalar oluşuyor verdiğiniz çizimle
Çözdüğü analiz %99,9 yanlış zaten
Merhaba Arkadaşlar!
Siz modele nasıl ulaştınız? Verdiği linke girince "dosya sahibinden erişim izni iste" dedi sistem. İstedim. "Mesajınız alındı" dedi. Sizin mailinize kaç gün sonra modeli gönderdi admin?
I can’t get geometry
RC model
link is not accessible
Helloo...I need help with a flow simulation for my final year project...i followed your video and tried doing it myself but i am having some issues after the meshing process. Could you please help me out??
Muhafiz Ghoghari ap kis project pe kaam kree thee?
i have this problem, help me: Error: GENERAL-CAR-CDR: invalid argument [1]: improper list
Error Object: 0
I have the same problem. Did you solve this Problem madam.
My software is Ansys student version.... i am unable to proceed fluent... how can i do that?
you couldn't execute 'setup' process?
Hi this was a really nice tutorial.
But I am having difficulty with the results. I get blue streamlines of zero velocity. I tried to follow at the steps. Can you please help me pinpoint my mistake or if i missed something. THanks
may I help you to find the result
may I help you to find the result
Aerospace Technologies thank you very much for the offer. I'm wondering how to model the aircraft better. your model doesn't seem to be really accurate but gives a great idea of how to go about it.
can you please some light on the modeling aspect.
Regards
contact Facebook ID- furqann00@gmail.com
Aerospace Technologies Ghani Khan. Is that the profile?
hello buddy please post the igs file link
you can use online communities such as grabcad or simscale, you'd find many such(even better) cad models from there for free.
I dont see any purpose of your results 😕
waste of time...
Bad job man. Work on it again. No summetry, no subtraction of the solid body, too small enclosure, not taking into account that you are on the supersonic flow region. Horrible. Sorry if I am harsh, but that's it.