sir, can you make a tutorial on a some NACA profile and analysis of various tip clearances, various pitch to chord ratios and incidence angles

sir, can you make a tutorial on a some NACA profile and analysis of various tip clearances, various pitch to chord ratios and incidence angles

sir can you make a tutorial on a some NACA profile and analysis of various tip clearances

sir it's CAD model making process available kindly any one help me

The final result is asymmetrical and doesn’t feel right

Too bad convergence and big difference between design point and characteristics

Sir if in multiple axial compressor my first rotor has 20 blade and last s4 has 90 blade and I want to input mass flow rate is 50 in actual condition then how much mass flow i can write in expression

what is the password for the file, please tell

and how expression mass flow rate value change in final cfd post result?

sir, i am working to make my own compressor setup but i dont know that is my no.of blades suppose 34 so that it is necessary to takemassflow rate @ r1 inlet is 34 ?

How did you calculate the refrence area?

Hi! What data does the report contain? is there any explanation on how the inlet and outlet pressures were calculated?

Nice, hope for more tutorials

Hello sir can you pls send this file if possible it will very user for me

Can you validate inlet mass flow rate, assume we just give total pressure at the inlet

Password

Hi there, amazing video, may I ask why you multiplied the mass in and the mass out by 10 at the end? I thought they give the values to you as kg s^-1 already Edit: I think I figured it out, is it because you are simulating only 1 of 10 total periodic segments and must multiply by the number of segments for the total flow?

Mach Number increase in the divergent portion of CD nozzle. How come mach number is highest in the throat? Is there some mistake?

if you add rotation velocity to static stuctural does it take into account the effect of coriolis forces?

Hello, I am doing a CFX on rotor/stator analysis on axial compressor. The physics check from ANSYS agree with my design and mesh checks are all within appropriate values, when you open the menu for mesh statistics. The meshes are saved and are detailed enough for both rotor and stator. However when I connect the turbogrid systems to CFX to input both components, even though Ive used same mesh size and detail for both of them, ANSYS CFX does not recognise the stator S1 mesh. IT is...there... I also then tried openning CFX on its own and inputting the ".gtm" saved mesh but still the same error. I cant do my CFD that way and nobody on internet managed to help me so far. Any suggestions that I might be missing. I would appreciate it if you would attempt o explain what might the problem be. WHAT I BASICALLY DID: I started from bladegen ( where I made R1 and S1, twists at root, mid, and tip, beta inlet and outlet angles through the Ang/Thk Mode entirely, and for model properties I marked R1 as axial compressor and S1 as diffuser, obviously R1 rotating and S1 stationary), then connected to separate turbogrid systems (to create meshes until I see no errors or at least 99% OK values in mesh statistics bar) and then CFX for high turbulence compressible flow CFD analysis, with most of the solver settings on, such as turbulent eddies, velocity compensations, and other type of settings. My issue is that my S1's mesh even though is approved by ANSYS turbogrid can NOT be seen by CFX - AT ALL! Thank you in advance!

thank you a lot!

hello, i am learning ansys cfx but **i don't know** how to use **(inflow/outdlow boundary tamplets) **and **(expression) in cfx pre** and it is hardly important for me so can you make a separate video on it, please??

tenk u so much bro tukish people are grateful to you

please blade hot to cold tutorial

Hii, can you tell around which mach speed is this epxperiment done? I need to do it at mach 5

If anyone is having trouble getting CFX to work,... you'll need to run CFX as administrator first, than map the file path for the workbench directory, using the folder ICON in the upper right corner, in my case it's R1 2024,... while CFX is running, start workbench and open the folder for the workbench project for this tutorial and it will load right up,... otherwise you get the error shown earlier.

scroll compressor please

anyone know the password?

Damn the voice is absolutely brilliant. So Boomer is a CAE engineer.

can you share the password sir? it's urgent pls

i like it

Respected Learn CAE Channel, Please make Millions and Billions of videos on CFD , FEA AND CFX Analysis in ANSYS its my kind and humble request and especially do more videos in Bladegen and CFturbo , ICEM CFD , Turbogrid in ANSYS as well as videos on CFD and CFX Analysis of Car Turbocharger , Radiator , Exhaust Manifold , Catalytic converter , Car and Building HVAC system CFD Analysis and many other flow Analysis in ANSYS.

Can you please share saprate video that how you create that four rotor and stator geometry and mesh

Hey, thanks for the Video. Maybe its a dumb question, but where do you get the formula for the efficiency from?

what is the pass of files!

Just for clarity is this compressor restricted to being coupled with a turbo or it can be used as a refrigerating compressor as well?

bro why i am not getting the enclosure ? It is showing me an error of manifold in geometry. Please help me what to do

Great video! loved it!!

can you give me a password plzzzz

so amazing thank you

what is the password of files???

Revolve (18) is revolved as sheet body, not solid body. How did you make it solid body ? You cut that part from your video

Brother, i am also working on similar type of CAD geometry but, when i am trying to mesh i am having an issue with the topology sharing, also when I am trying to do it in a different way it is giving me intersecting surface meshes or close to intersecting error and its generating a failed mesh, need your help regarding this

Can you do a video on how to design a radial inflow turbine for a micro gas turbine please? Using Ansys Rtd

✔️ P r o m o s m

I have one doubt it will be a great if you help me In cantilever beam force applied is 4N at free end axially.If i apply this force on each node wheather i have to apply 4N or i have to divide this force by total no of nodes on cross section and then apply it.

Hey, I am about to start a 3D analysis of an airfoil with a set of vortex generators on top of it for supersonic flows. Can I refer to this tutorial cuz the missile too has sharp extruded faces on the top (just like my airfoil having the vortex generators on top) and bottom and I really can't seem to mesh my model for the vortex generators especially.

I have a model of Francis turbine and need to use periodic mesh for inner blade (24 identical blades) and then repeat it, how do I do that?

Plzzz do a video on CFD analysis of a nose cone of rocket 🚀 ....sir Only nose cone part using CFD analysis

Can u make campbell diagram for whole compressor blade