Rotating airfoil simulation - Fluent ansys - CL, CD?

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KikoAzor posted this 4 days ago

Hello guys, I am in real need, I am working on my diploma thesis and the deadline is really close. I am having a bit of trouble with getting correct results of CL and CD from simulation over a rotating airfoil.   This is what I did so far: I followed this video on youtube: 

?v=G0zAHv0rEa8 to make the rotating aifoil by creating to interface zones one is fluid, and the other one is inside of it - rotating - and inside this one is my airfoil as a rotating wall... My airfoil´s chord line has 1 meter. I situated the airfoil in the middle of the rotating circle... I set the rotation of the rotating part -0,5 radians... time step is 0,005 and the number of timesteps is 200.. Simulation is fine just my values of CL and CD are crazy high, I dont know where I could make a mistake. Here is the picture of the lift curve generated by fluent in "report definitions".. If there will be need to upload any other screenshots just let me know. If anyone would be able to get me out of this desperate situation I would be very grateful. Thank you

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kkanade posted this 4 days ago

can you please insert image of cl definition. 

KikoAzor posted this 4 days ago

Hello kkande, thank you for your response, here are the PrintScreen of cl definition

veera posted this 3 days ago

did you checked the reference values ?

 

KikoAzor posted this 3 days ago

https://ibb.co/rx1qWt8

here is the link for the reference values I set... I used the one from inlet... should I change something? thank you

veera posted this 3 days ago

yah for estimating cl and cd we have to set that object area instead of default one . , i think so .. just try 

i am not confirm and also try with different model 

KikoAzor posted this 3 days ago

Thank you veera, it was like you said I forgot to set the reference values zone.. Now its working fine....Thanks a lot for your ideas fellas  

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