NACA airfoil aerodynamics forces
Hello everyone;
I am doing some 2D CFD simulations on a NACA airfoil and trying to estimate the lift and drag forces using Fluent -13......I have managed to set up the domain as per the experiment( obtained from a journal paper) and the lift forces are being predicted accurately but my drag coefficient is nearly 10 times higher than expected.....I am running simulation at low Re and using the k-w SST model ... I am sure this problem was seen before in FLuent 6.3 , could someone pls tell me whether this is resolved in Fluent -13... Thanks in advance Joseph |
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Regards |
Thanks for the information.....yes earlier I was using an unstructured mesh in the analysis ...I am now trying with a hybrid mesh and now the problem seems to be the exact opposite , I am getting a good result for the drag coefficient but a poor result for the lift coefficient....could this also be due to the mesh...Btw my wall y plus values are between 10-15.....One further question would be the reference values for a 2D simulation....does the length correspond to chord length and area for a 2D case correspond to chord length also...
Thanks Joseph |
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Thanks a lot for your reply.....the 2D analysis appear to be fine now but just one further question is there any way to keep the wall y-plus value from fluctuating throughtout the iteration process becuase I have noticed that it is within acceptable range at the begining of the calculation but later on increases......Thx
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