Wing with different airfoil section

[aweproject2023]

Hi,

I was running Wing example everything is fine. However, I wasn't sure how to apply different airfoil section in the script (wing.jl). Thx!

[aweproject2023]

How I can change the airfoil (RAE 101) profile used in the example to different airfoil shapes?

[EdoAlvarezR]

Hi Peter!

The "Simple Wing" tutorial shows how to pass the airfoil polar to the force calculation function, which is also shown in Line 170 here: LINK.

The file name of the airfoil polar refers to one of the airfoils in the default airfoil database that comes with FLOWUnsteady under database/airfoils. See the slides under the Propeller tutorial for more details on the database.

Alternatively, you can define your own database and pass the directory of the database to generate_calc_aerodynamicforce using the following keyword argument:

uns.generate_calc_aerodynamicforce(; add_parasiticdrag=true,
                                      add_skinfriction=true,
                                      airfoilpolar="myairfoilpolar.csv",
                                      parasiticdrag_args = (; read_path="path/to/my/database/airfoils")
                                      )

The polar file can be any polar downloaded from airfoiltools.com, generated through XFOIL, or that you have created yourself. For instance, here is what the RAE 101 polar file looks like: LINK

[aweproject2023]

Awesome. Thank you so much!

[christianhauschel]

Am I right to assume that the polar cl values are not used in the calculation of the bound vorticity?
I.e. cambered airfoils would not be modelled accurately?

[EdoAlvarezR]

Correct. Cl of the polar is ignored in the wing model and only Cd is used.

[dlmmssm]

Hi, how can I calculate a wing with asymmetric airfoil? Pre-Twist the airfoil section by the zero lift angle?

Correct. Cl of the polar is ignored in the wing model and only Cd is used.