ANSYS Fluent: NACA 2412 airfoil with Angle of Attack Rotation and Varying Inlet velocity
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- เผยแพร่เมื่อ 8 ธ.ค. 2018
- The following video shows the ANSYS fluent procedure for NACA 2412 airfoil. the primary aim is to get the Coefficient of Lift and Coefficient of Drag values for varying Inlet velocity, but a constant Angle of attack, and, Varying angle of attack and a constant velocity. This project is being done using "Parameters set". Both the simulation can be done at once using Parameter sets.
Nice. Great video until the very end where there were some mistakes but still EXTREMELY helpful. Thank you.
Hi,
Firstly many thanks for your video it was very helpful, but when you click "update all design points" it does not work at all.
Could you help me how to solve?
The error says:
(DP 18) The Mesh component in FOLDER_NAME for Design Point 18 requires user input before it can be updated. For instructions on how to address the cell in its current state, click the blue triangle in the lower right corner of the cell in the Project Schematic. Set the design point as current to see the state at the point of failure.
Thank you in advanced!
Thanks for the nice video tutorial. Do you have any tutorials of plasma actuator on airfoil or flat plate?
Simple and clear work thanks VERY much , you have helped me a lot BUT a note ! : You have forgotten to show us at the final step (in design modeler ) that you have changed your surfacic domain from SOLID to FLUID. If we don't do that , we can not do meshing for airfoil.
I hope my note will be helpful for others peoples who read it. THNAKS YOU AGAIN !
where is the option for changing surface domain to fluid?
@@stanko299 Hi click on your surface or volume body ( show the tree ( parts , bodies) ; a details vew appears below , change solid to fluid domain
hi
in the inlet boundary condition if i change the angle of attack by change the directional vector.like below
for example
X-direction 1
Y-direction 0
which is 0 angle of attack. right?
X-direction 0.97814760073
Y-direction 0.20791169081775931
which is 12 degree angle of attack. right?
if i change the AOA, do i have to change the axis for the life and drag?
Why did u take triangular element. Will it give correct result?
I did everything the same way, but at 7 minutes I pressed the create command and got an error.
invalid profile selection.
Can you help me?
Hi guys, my results are differents of the video. In the mesh I made the same video but it was visually different
- stayed solid - i dont know if this can to change the results.
Thanks🙏
How to work parameters I don't get a result.. Can u hear me
M not getting the whole mesh correctly in the rectangle drawn...its only coming to hemisphere
What to enter the new parameter sir
What we can do after these steps..
You didnt describe about angle of attack parameter
Please i have a probleme, when i try to upload the coord_file for the 3D curve it shows me an error "error reading coordinates file " even i did the same process as yours. If you have any idea about this please tell me
you need to check your default decimal separator, it needs to be same in excel and in ansys
Merci
Can you please make a video on Analysis of aerofoil (NACA0012) with gurney flap in CFD
it will cost you Rs. 15000 bro
can u plz do my project
why have you taken areas as 0.4 and 0.5 , have you already divided it by 2
@Kevin seems like he misprinted 0.4 instead of 0.5: the denominator has a factor of half (0.5)
Its not transient . Is it laminar? U didn't use inflation or y+ in ur meshing . Plz explane about transient state
What Reynolds number did you use in your problem?
the tutorial involves changing of inlet velocity too, thus changing Reynold number. but you can calculate Reynolds number by: Re=(density * Velocity * length)/dynamic viscosity.
For P5 why did you use 0.4?
I NEED ANSWERS!!
i love you
como calcular los coeficientes de lift y drag
Cl=L/(0.5*ro*V^2 * S)
CD=D/(0.5*ro*V^2 * S)
@@xxroco0418xx Did he really use the S? Didn't see
@@olooalfredo s=1 here