Thank you Andre for the update! One question though, what is the 'From zero' box doing when you tick it in the analysis range? I don't understand what is it about, thanks in advance, keep up the good work :)
In my experience, XFoil converges more easily if it starts a sequence from a low aoa value, where the BL has low thickness. Starting with a high aoa forces XFoil to find a solution with potentially high flow separation, which is more difficult.
Thank you for the videos. I have one question. If I need to simulate an airfoil with C=0.5m (I can import the coordinate (.dat) file), how I will set the point about which moment is acting. In XFOIL it is default 0.25, if we chose an aerofoil of unit chord, not at 0.25C. That is even if the chord of airfoil is less than unit length (say 0.5) the location will be at 0.25 (ie., at 0.50C of the airfoil). But there is a command in xfoil (CMXY) to control this. How I will do that in XFLR5?
There is a problem on the calculation of the tail volume if the wing is not at the origin. Does this also affect other calculations? I am sorry if you have already fixed this, I have a slightly older version of xflr5. By the way, thanks for the tutorials. They helped me a lot in the design process. :)
Thanks for the prompt reply. I didnt mean to ask if the incorrect tail volume calculation affects any thing else. I mean to ask if this bug itself alters any other calculations besides the tail volume.
Informative video. One question though: Is there a way to find out on which exact curve is the erroneous point. I mean how to know which curve has that point of almost zero Cd if there are huge number of polars at display at once
The video is informative and really helpful. But I have a problem in loading wortmann airfoils where airfoil shape distorts when .dat file of wortmann downloaded from airfoil tools is directly loaded.
Thank you so much for these videos!
Encore un gigantesque merci pour cet outil et toutes ces infos ! MERCIII ! ;)
Thank you Andre for the update!
One question though, what is the 'From zero' box doing when you tick it in the analysis range?
I don't understand what is it about, thanks in advance, keep up the good work :)
In my experience, XFoil converges more easily if it starts a sequence from a low aoa value, where the BL has low thickness. Starting with a high aoa forces XFoil to find a solution with potentially high flow separation, which is more difficult.
That makes perfect sense. Thanks for the explanation, I will change the way I perform my analisys :)
Thank you for the videos.
I have one question. If I need to simulate an airfoil with C=0.5m (I can import the coordinate (.dat) file), how I will set the point about which moment is acting. In XFOIL it is default 0.25, if we chose an aerofoil of unit chord, not at 0.25C. That is even if the chord of airfoil is less than unit length (say 0.5) the location will be at 0.25 (ie., at 0.50C of the airfoil). But there is a command in xfoil (CMXY) to control this.
How I will do that in XFLR5?
How do I get the exact point of maximum cl? instead of just using some eye judgement?
How do you get the polar graph to show up in the polar view? I did the analysis but the XLFR5 cannot seem to generate graph only in the polar view
There is a problem on the calculation of the tail volume if the wing is not at the origin. Does this also affect other calculations? I am sorry if you have already fixed this, I have a slightly older version of xflr5.
By the way, thanks for the tutorials. They helped me a lot in the design process. :)
RIght, I'll correct it in the upcoming version. Note that the tail volume value is not used in the calculation, it is only provided for information.
Thanks for the prompt reply. I didnt mean to ask if the incorrect tail volume calculation affects any thing else. I mean to ask if this bug itself alters any other calculations besides the tail volume.
No, it is just calculated and displayed for information. No other usage.
Informative video. One question though: Is there a way to find out on which exact curve is the erroneous point. I mean how to know which curve has that point of almost zero Cd if there are huge number of polars at display at once
Unfortunately, no other solution than identifying the curve color in the legend.
Does the version Different the convergent of airfoil Calculations hope answer
The video is informative and really helpful. But I have a problem in loading wortmann airfoils where airfoil shape distorts when .dat file of wortmann downloaded from airfoil tools is directly loaded.
is there an option to calculate without flow seperation?
Only for the inviscid part of the foil calculation.
Otherwise flow separation is an integral part of XFoil.
what is the Cm?
Pitching moment Coefficient , i got ya
@@thanasistheofilopoulos803 thank you, too late.