What exactly does batch analysis do and what is it used for? Is it necessary to do batch analysis when designing an aircraft? What exactly do I need to understand from the graphs I get when I do the analysis?
A batch analysis is used to analyse a broad range of airfoil at the same time. Based off your results, you can select the airfoil suited to your needs.
I'm having the exact same problem. All the lines from the naca are red and all the lines from GP25 are green in my case, but i cant differentiate between their own reynold variations. EDIT: on the small side window called "direct foil analysis", make sure the "flow down style" box is not checked. If it is checked then all the lines will have the same style. I just tested a new file with the box unchecked and now it looks just like the video above.
I have a problem with the cp location in xflr5.On condition that the angle of attack increases, the cp location will come to near the front side of the wing, but in my program, the cp location does not come to the front side of the wing on the contrary my cp location goes backward.
It only converges some airfoils and doesn't converge some.. I've tried changing all ranges of AoAs are Reynolds numbers but its still not converging at any point.. Plz help.. Thanks
XFoil sometimes converges and sometimes it doesn't. The parameters which affect convergence are the panel density (F3) and the settings for free and forced transition.
I select the two aerofoils but I think it just conducts it to one of them as it doesn't show on the left side of the screen the name of the aerofoil and it's Reynolds number just like yours?
There's no reason it should analyze only one of the airfoils. Double check that both are selected. It could also be that one of the analysis fails for some reason. What does the log file say ?
hello, recently I met a problem of loading the airfoil .dat file to XFLR5. I export the .dat from profilli-2, and it turns out that if the file size is approaches to 9kb, the XFLR5 can not load it, but it can when the file size is about 1 or 3kb. Is there a way that I can always access to a small size airfoil .dat file? Besides I was wondering if it could be solved in the future release.
I suppose you are hitting the hard-coded limit of 300 points max which can be handled by XFoil. And unfortunately because it's hard-coded, it can't be changed.
Un-check the "update polar view" checkbox. Sometimes the background update of the graphs cannot keep pace with the analysis, and this leads to crashes. There have also been some improvements to multi-threaded analysis in the latest versions of the program.
Brilliant Videos. Thanks very much
What exactly does batch analysis do and what is it used for? Is it necessary to do batch analysis when designing an aircraft? What exactly do I need to understand from the graphs I get when I do the analysis?
A batch analysis is used to analyse a broad range of airfoil at the same time. Based off your results, you can select the airfoil suited to your needs.
@techwinder How to get that Re Range option (0:26) in the latest xflr5 v6.57 ?
I can't find it, it only gives Re List option.
I ma also facing this issue @Jayesh Rajam. If you have found a solution kindly do let me know. Thanks
When I do a batch analysis, all the lines in my graph are the same color! what should I do?
I'm having the exact same problem. All the lines from the naca are red and all the lines from GP25 are green in my case, but i cant differentiate between their own reynold variations.
EDIT: on the small side window called "direct foil analysis", make sure the "flow down style" box is not checked. If it is checked then all the lines will have the same style. I just tested a new file with the box unchecked and now it looks just like the video above.
@@DaniUsagiThanks !!
I have a problem with the cp location in xflr5.On condition that the angle of attack increases, the cp location will come to near the front side of the wing, but in my program, the cp location does not come to the front side of the wing on the contrary my cp location goes backward.
in this case main idea is making analysis together isnt it?
It only converges some airfoils and doesn't converge some..
I've tried changing all ranges of AoAs are Reynolds numbers but its still not converging at any point..
Plz help..
Thanks
XFoil sometimes converges and sometimes it doesn't. The parameters which affect convergence are the panel density (F3) and the settings for free and forced transition.
hi, the lines on the graph are all the same color. how to set different color assignment for each drawing
I select the two aerofoils but I think it just conducts it to one of them as it doesn't show on the left side of the screen the name of the aerofoil and it's Reynolds number just like yours?
There's no reason it should analyze only one of the airfoils. Double check that both are selected.
It could also be that one of the analysis fails for some reason. What does the log file say ?
how do populate the re number list automatically?
Hi, when I try to run inviscid analysis I don't see the polars. Could I be making a mistake somewhere or is this what should happen?
I think drag will not show up in an inviscid analysis
hello, recently I met a problem of loading the airfoil .dat file to XFLR5. I export the .dat from profilli-2, and it turns out that if the file size is approaches to 9kb, the XFLR5 can not load it, but it can when the file size is about 1 or 3kb. Is there a way that I can always access to a small size airfoil .dat file? Besides I was wondering if it could be solved in the future release.
I suppose you are hitting the hard-coded limit of 300 points max which can be handled by XFoil. And unfortunately because it's hard-coded, it can't be changed.
I see. Thank you
Does someone has a good online database to find airfoils? Some of them found on airfoiltools have some problems with coordinates
the .dat files are sourced by citation in airfoiltools when youre in the page and you can follow back to where they get coordinates,
The program crashes every time I try to perform a multithreaded batch analysis. What should I do?
Try doing a Batch Analysis first and the do the Multi-threaded one.
Un-check the "update polar view" checkbox. Sometimes the background update of the graphs cannot keep pace with the analysis, and this leads to crashes.
There have also been some improvements to multi-threaded analysis in the latest versions of the program.