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how to generate an XY plot for lift vs airfoil chordlength?
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.
Regards, Basil -
how to generate an XY plot for lift vs airfoil chordlength?
thanks, i new to cosmosflo so can't really understand . is there any tutorial close to what you mentioned?
cheers
TS-
how to generate an XY plot for lift vs airfoil chordlength?
Everything you need you can find in a standard tutorial on FloWorks (especially look at Cylinder Drag, Mesh Refining etc)
Regards, Basil
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how to generate an XY plot for lift vs airfoil chordlength?
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.
pls enlighten me, anyone?
TS-
how to generate an XY plot for lift vs airfoil chordlength?
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.
Rich.
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how to generate an XY plot for lift vs airfoil chordlength?
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.