Hi, i'm currently using floworks to simulate a NACA0015
aorfoil. i managed to run the solver with results calculated.
however, i am unable to generate an XY plot for the lift force vs
the chordlength, any pointers?
Create the configurable part, assign several configurations
with your variable parameter, clone the project, perform a batch
run and get a lift force for all of them. That is true if you
cannot use the DOE.
i tried using the cylinder solid and managed to generate the
XY plot, however, i draw the same cylinder and extruded the circle
to create the same cylinder solid, sadly, nothing was generated
when i create the XY plot after solving.
Question:
after drawing the surface using solidworks or importing from a DWG
file, i extruded the base of the surface to create a 3D solid
cylinder. Do i need to do anything else before i continue creating
the cosmosflo project? If really that i missed another step before
creating cosmosflo project, that could be the reason why i am
unable to generate XY plot with my airfoil simulation.
the xy plot function works with a line. the x dimension
travels along the line and the y dimension is the value of the
variable that you selected. define a line on the surface and then
you should be able to create the xy plot along that line. I've done
this after running the solver and it was able to create the plot.
In other words, you should not have to re-run the solver.
the help text for the xy plot should also be helpful to you.
Me, the Late comer:
Hi Tan. I saw this and was interested because I have done it with
an NACA 230000 series airfoil. Rich is correct. You can open a
sketch on an end face of the airfoil, and use "Convert Entities" on
the airfoil upper surface (really, an edge). Open another sketch on
the face and do the same for the bottom edge. Now you have two
sketches from which to generate XY graphs. I chose to graph the Cp
pressure coefficient, and you can match the graph-up with actual
published CL diagrams for that airfoil.
Regards, Basil