[ptaqu]

Hello CFD-Online community It's my first post so please be gentle
I am trying to obtain lift and drag forces for 3d wing (dependent on Angle of Attack (AoA). Wing is from rc plane model - so no profile data for validation (at least i think so).
I created 3d model of wing in Solidworks (symmetry half of the wingspan = 0.8 m, chord 0.28). Then in Ansys Mesher i created flow channel (i attached it below).
Flow channel have following boundary conditions: velocity-inlet, pressure-outlet, half of wing as wall and symmetry wall.
The dimensions are: length channel - 20 m, height - 10 m, width - 6 m. The velocity of rc model is from 10 to 20 m/s (Mentor by Multiplex).
I compute lift and drag forces with k-epsilon rng, k-omega sst with low re corrections for velocity-inlet parameters set as 10 m/s normal to boundary.
I have few questions:
1. When channel have velocity-inlet can I change AoA by changing parameters of X and Y parts (sin and cos) of velocity or do I have to change AoA by rotating my half-wing ?
2. In 2D cases I saw C-grid mesh connected with ideal-gas and with far-field conditions (it's called maybe open channel). How to translate (or do I need that) this case to 3D with low Re numbers < 400 ?
(calculated here)
http://airfoiltools.com/calculator/r...ber?MReNumForm[vel]=20&MReNumForm[chord]=0.28&MReNumForm[kvisc]=1.5111E-yt0=Calculate
3. Are dimensions of flow channel ok ?
Greetings
Ptaqu