Simulating airfoil imperfections or contamination in 2d

Justin.Martin · April 9, 2019, 01:36

Hey guys,

Working with Xfoil/XFLR5 and SW flow analysis, is there a good way to simulation a contaminated leading edge, or airfoil imperfections in 2d, and get semi-reliable polars?

I typically work in Xfoil/XFLR5 for airfoil modifications or design. My current project is geared towards the experimental aircraft market. I am trying to ensure that The modifications I am making wont overly impact airfoil performance, as is the case with many laminar airfoils.

Ncrit values adjust the turbulence of the air mass, but not the imperfection or contamination of an airfoil...

You can force a transition at x.xx position, but that seems to act more like forcing transition into high energy vortex. I may be wrong on this, but I tend to get high Clmax polars when forcing the transition, not significantly lower as is the typical case real world.

Any ideas?

Justin.Martin · April 9, 2019, 01:41

I should specify, I am working Re range 1.75m-9.5m mach 0.3 and standard 1.225kg/m^3, kinematic viscosity 1.5x10^-5 m^2/s.

Justin.Martin · April 10, 2019, 15:16

bump?

There has to be some kind of answer here...

April 9, 2019, 01:36	Simulating airfoil imperfections or contamination in 2d	#1
Justin.Martin New Member Join Date: Apr 2019 Location: California Posts: 3 Rep Power: 7	Hey guys, Working with Xfoil/XFLR5 and SW flow analysis, is there a good way to simulation a contaminated leading edge, or airfoil imperfections in 2d, and get semi-reliable polars? I typically work in Xfoil/XFLR5 for airfoil modifications or design. My current project is geared towards the experimental aircraft market. I am trying to ensure that The modifications I am making wont overly impact airfoil performance, as is the case with many laminar airfoils. Ncrit values adjust the turbulence of the air mass, but not the imperfection or contamination of an airfoil... You can force a transition at x.xx position, but that seems to act more like forcing transition into high energy vortex. I may be wrong on this, but I tend to get high Clmax polars when forcing the transition, not significantly lower as is the typical case real world. Any ideas?

April 9, 2019, 01:41		#2
Justin.Martin New Member Join Date: Apr 2019 Location: California Posts: 3 Rep Power: 7	I should specify, I am working Re range 1.75m-9.5m mach 0.3 and standard 1.225kg/m^3, kinematic viscosity 1.5x10^-5 m^2/s. Last edited by Justin.Martin; April 10, 2019 at 15:15.

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April 10, 2019, 15:16		#3
Justin.Martin New Member Join Date: Apr 2019 Location: California Posts: 3 Rep Power: 7	bump? There has to be some kind of answer here...