CFD study on airfoil, ANSYS
Budget: ₹100 – ₹150 INR
Do the aerofoil alone CFD, for few angle of attack say 10.75 deg, 8 deg, 6 deg, I would be personally interested in Knowing the effect of cascading aerofoil with gap between aerofoil kept at 0.03C, 0.06C, 0.09 C, and 0.25 C. So it will be 12 Cases, with forward velocity 45 m/s, You can give me your best quote.
the blade will looks like.
THe figure is in attached file
The angle of attack is 10 degree 45 minutes. At this angle of attack, lift co-efficient (CL) is 1.485 and drag co-efficient is 0.06525.
the blade will looks like.
THe figure is in attached file
The angle of attack is 10 degree 45 minutes. At this angle of attack, lift co-efficient (CL) is 1.485 and drag co-efficient is 0.06525.