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drag valus is illogical and the solution has not converged

could you upload the cad of the Rc plane

the enclosure is a joke, particularly that you chose to keep the faces adjacent to the wingtips as wall and not symmetry or an outlet. You only end up getting exaggerated results owing to narrowed enclosure around the model.

Isks pdf milega kya ?

Вот ответь мне на вопрос , зачем тебе ансис , если ты построил самую плохую модель из всех возможных, с большими потерями на балансировку и большой омываемой поверхностью ? Линии посмотреть ? Или кнопочки понажимать ? Ты абсолютно не умеешь пользоваться этой программой и не обладаешь базовыми знаниями и опытом .

Machine?

Hi quick question. I am at the point where I get my drag and pressure graphs and when I am in the contour options it wont let me see the inernal boundary conditions and therfore wont let me select the contour of my plane/wing part. I cant see the interior air either so what can I be doing wrong. I would really like contour of the wing.

How to find vortex flow brother...

can you leave the link of geometry in description?

He is not selected Boolean ean

Greetings, how was the geometry of the plane designed? Is it using the Insight program or another program was used, kindly I need a video of how to design the plane

Why is the enclosure so small? What should be the proportion between the virtual wind tunnel (enclosure) and the model be?

Thank u for this video. I have a problem. I did as you did but ' cl cd cm ' values ​​were calculated incorrectly. Do you have any idea about this problem?

Why does the drag coefficient is negative?

Can you Explain how we can get Stability and Control Derivatives for Different angle of attack, slide slip angle, and mach number.

Hello this a good video. But I want to ask that the model imported to geometry is just a shell? Or could i import a model with full solid or structure inside?

Sir final year project Windmill single blades ansys cfd step by step draw pnu slu sir and pressure and velocity calculation

Thanks整挺好👍👍👍

Geometry???

The real challenge is if can you make the entire solid origin symmetric. Meaning the distance from each vertex to the origin is the same.

Bro, How ı can "" Cl "" Lift Coeffience

what if you analyse half of the geometry? would the coefficients of drag and lift be the same?

🔥🔥🔥🔥🔥

Bro I have searched a lot . But I think your video is awesome. With so many tiny details and accurate dimensions I completed the hammer in catia . Now with the help of blueprint I am going to make a wooden hammer. Thank you so much.

Thala....neenga design panna... varudhu...na pannalum varudhu..but vera mariii... varudhu ☺️☺️

✌️✌️

Ultiiii

Super da

Super video ji😍😍

some thoughts. it is not clear whether you have accomplished anything, here. it is not clear whether the velocity has been set too low --- there appears to be, essentially, NO lift or turbulence, predicted. it is not clear whether the program has treated the aircraft as being FIXED in space. it can be understood that a simulation of air flow past an airframe is not IDENTICAL to what happens, When an airframe Moves through air. clearly, the asymmetrically shaped nose WILL produce nose-Down moment, in flight. since this design has no real fuselage, you have NO fuselage-related data. the design of the stabs is less-than Normal/optimal. cheers googletranslate

Super video bro

Thanks jii.. Very useful

Verithanao verithanam

Nice da

Super bro,Voice kudunga bro,then only understand easily,

Keep it up

Oru kelvi

good bro its usefull

nice da keep doing

Mechon'$💪

Keep Going Dudes

nice bro keep doing

Keep Rocking...

Super👌👌

Super...Bro keep doing

Explanation is super..... Keep going

Thanks soon more interesting video will be posted

Super 😎

Mass mass masss