NACA 0012 (3D) strange results?
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Hi friends!
Im new on this forum, I've started learning fluent because i need to make a final project designing a plane for my final degree. I am starting with a NACA 0012 (in 3d ). Firstly i am introducing a velocity inlet of 30 m/s, and inviscid flow model. I have done it with 0 AngleOfAttack ( on boundary conditions X=-30 m/s) With 5 AOA (X=-30 cos (5), Y=0, Z=-30sin (5)) and with 10 AOA (X=-30cos(10), Y=0, Z=-30sin(10)) I have attached 3 plots of velocities for the three angles, I think it is really strange that the stagnation point (where the velocity is 0 m/s), when I change the angle of attack does not varies. Are these results bad? The other two plots show the coefficients of pressures around the naca (for this part I have created an Iso surface, selecting mesh and Y coordinate from the airfoil surface). For the results, I think there is almost no difference and it should be more difference. Moreover, the results for 5 AOA (Cd=0.027117317 and Cl=0.30893708) 10 AOA (Cd= 0.10493012 and Cl=0.59508828 ) I think that the value of the Cd (0.10492012) is not very reasonable. What do you think about the results? Thank you :):) |
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