Possible low lift forces
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I'm a member of the Aero Design team of my university and we are developing the wing of the model. When I simulated the lift and drag forces I got the following results: LIFT = 10.3 [N] and DRAG = 0.3 [N]. Are these results accurate?(AoA 0)
Since the sizes of the wing are: wingspan = 1050 mm; area = 0.45 m2 ; chord = 185 mm.
The foil got a high lift coefficient on XRFL5 (close to 1.2 at AoA 0).
The velocity used in this simulation was 8m/s (average cruising speed)
I'm new to Ansys Fluent, so I used this setup:
THANK YOU!!
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