techwinder is just my private folder. I think I remember downloading the airfoil database from tracfoil.com/airfoils/index.php?page=en many years ago. There is this one also :m-selig.ae.illinois.edu/ads/coord_database.html I take note of the other suggestions and will try to make the steps more explicit in a future video. André
Hi, firstly love what you've done with the tutorial. But for some friendly feedback, already after changing the panels, opening a new airfoil, where is this tech winder folder with all the airfoils files? Is it included with the XFLR5 download or is it found somewhere else? On the website? A third party website? Can't find this folder. Would be good to have an explanation somewhere in the beginning about everything needed for the program. Also, it would also be good if you could say things like "let's design a naca airfoil by clicking on the design tab and clicking naca foil" or "re-panel the airfoil by clicking the design tab and clicking redefine globally" its a bit tedious having to just follow visually pausing the video and switching from the video to the program for those of us with one screen only. Again, nice job overall, just little things to make things feel more smoother.
It's all well and good for someone who is familiar with the mechanics of the program. I wonder how long it took for you to become familiar with its features and functions. Jumping about as you do so quickly is of no help to a neophyte trying to analyse a cuff for the leading edge of my plane for better STOL performance. I suppose the best answer is to get another plane.
NEED HELP..!! when i import a custom made foil from solid works, everything goes fine but when i run the analysis graph doesnt get plotted and it shows unconverged after 100 iterations but the main problem is that nothing gets plotted on the graphs.....please help...!!
usually if you just insert a graph from the coordinates the trailing edge of the airfoil is open, two lines aren't connected, so it can't run analysis on open foil
Hey, I have the same problem right now. Is there anyway I can connect the trailing edge? I did not import a foil btw. I used the design selection and made a NACA2314 . Don't know why it did not connect the trailing edge points...
In the analysis window, there are two analyses, one is alpha another one is Cl. But I could not the difference. I can just use alpha. What is analysis Cl for? In this video example also use alpha for the analysis.
Hello Sir, how can i see the graph of Cd with the analysis? Infact, for my exam i need the graph of Cd function of alpha.. How can i do.. Thanks for the answer.
Is there a tutorial for the combination of different profiles eg at the root ag24 and ag25 at the end ? Which rules are there for the alignment of different profiles on which axis ? Specifically explained in the program xlfr5. Thank you for answer, Joe
Hi sir! I can't understand the differences between type 1-2-3 and 4. I've searched about it on the internet but couldn't find any documentation. What is the difference between types in airfoil analysis?
Can u please elaborate about XTR top and bottom, trip location and N rit...???
5 лет назад
Can you analyze multi element airfoils with xflr5 ? (like naca 6412 airfoil with a naca 4412 flap etc) I tried to look for it on the internet but since I don't really know what I am doing at this moment, I couldn't really find anything.
It's an amazing video. But it's such a pity that I'm a Chinese, I can only understand a little. Do you have any other excellent design of electric glider? (I mean, based on XFLR5) I really need it. Thanks bro!
Hello André. For Naca 0009 analysis, panel number is 99 and there is a node at leading edge. But you re-panel the airfoil for 100 panels. After this refinement leading edge node is deleted and leading edge panel becomes perpendicular to the airflow at zero degree angle of attack. Is this good for the analysis? I mean did you do this (even number of panels) intentionally?
I did not run a controlled comparison analysis for a Reynolds number range yet. But i can say that leading edge node is essential for any numerical analysis.
You're right, but XFoil doesn't converge as well when the Mach number is non-zero. For the precision needed, I tend to find that the assumption of incompressible flow is acceptable, especially since the 3D panel analysis methods are also based on incompressible flow assumptions.
Hello! I have been trying to understand which Reynolds number we are entering at this stage (@3:50, Re = 100,000) and searched everywhere to try to understand but I can not find any information or definition for that Reynolds number. I am currently running simulations on a miniature model wind turbine (0.5m diameter) and if I base that Reynolds number on the chord length, I get an Re of about 12,000 which is very low and pretty much leads to little to no power from the turbine, and a quasi-entirely negative Cp. Can you please help me out if you know what that Reynolds number is based on?
Hello, Sorry for the late reply. I'm not sure I quite understand the question. If your wind turbine airfoil operates at 12k, that's the value you should set in the analysis. Re = V. Chord/Kinematic viscosity. The fact that Cp is
Thanks for this great playlist. I have a problem with panel viev. After I rightclick at foil there is no option to show panels. How can I make this work?
Hello Techwinder, I would like to ask for some help: how do I import a new airfoil model to XFLR5? I need to analise a wing using the Selig 1223 foil but I cannot find it at the foil base. Thanks!
A Panel is the line segment between two points.The foil is approximated by this collection of line segments. Increasing the number improves the approximation, and typically ~100 panels is enough for a good approximation.
helooo i need your help in this problem when i need analyze this wing ( NACA 2412 airfoil ) Wing (Cord is 152 mm , Span 225 mm area 0.035 m^2 ) at fixed speed 30 m/s what is the solv for this Problem pleas ((unconverged after 100 iterations out of 100 _________ Analysis completed ...some points are unconverged )))
I am currently trying to use xflr5 for NACA2412 and NACALS0417 but it either doesn't converge or there is a compressibility error. I've tried following your first step in terms of the panelling but that messes up/changes the shape of the airfoil, making the analysis pretty much impossible; is there any way you can help?
There's no reason for panelling to change the shape of the airfoil. Also from my experience, it usually only improves convergence. Compressibility errors usually arise when trying to set a non-zero Mach number. Unfortunately, I'm not familiar enough with the inner workings of xfoil, so for this error you would get more help from the xfoil forum @yahoo groups. If you can't work it out, please share the project file and I'll have a look.
Hi. I am having problems with installation of the file. Very new to this. I am running windows 7- 32 bit at my university. When I download the package. Do I just run the exe file? if so, when I do, xlfr5 opens but the entire file is blacked out. No menu. But if I go to the top of the program and click along the top line, the sub heading of the menu options appear. Even if a create a new, the entire program is there, its like its all there but blacked out. I tried changing the text colour. Thanks
I had the same problem with the latest version. You may need to do what Techwinder suggested in a reply to another comment. He said "Use the submenu CurrentFoil/setStyle, and choose an option for the points."
That's a very general question. The choice depends on what kind of flight you are targeting. Besides, I don't really want to give advice. The purpose of xflr5 is precisely to help you make your own design choices.
it shows "The application was unable to start correctly (0xc000007b). Click OK to close the application." I have tried many things, but nothing is working...pls suggest what can be done.
+jdomnhl17 I run 10.10.5 and have no problem. What exactly is the problem? You could try doing "Get Info" on the dat file (right click/command click) then "Open With", and select XFLR5 as the app to open it with.
+Hans Conser I figured out that when downloading the file from the airfoil database, Safari was saving it as a .txt file named "XXXX.dat." So that was the problem. I just switched to Chrome :)
@@techwinder where are there I couldn't find them anywhere, I have a study teacher ask for me these datas, do you have any VIDEO or SOURCE about these Cm0, Cl0....??? Could you share the link or address??
@@techwinder thanks you helped me so much , I have just one more question at cruise my Mach number is 0.8 should I write as 0.8 because most of the case it is written 0?????
I was waiting for a playlist like that for a long... Tanks Bro!
A hello from Brazil!
+Marcelo Henrique it is not installing for me. the file is just closing once it opens up
+Santhosh Kumar you can download the official website, try and tell me.
sourceforge.net/projects/xflr5/files/
+Santhosh Kumar it did'nt get installed in my pc
how is neymar bro?
Huge thanks mate, you've literally saved my life at uni, I owe you one
techwinder is just my private folder. I think I remember downloading the airfoil database from tracfoil.com/airfoils/index.php?page=en many years ago. There is this one also :m-selig.ae.illinois.edu/ads/coord_database.html
I take note of the other suggestions and will try to make the steps more explicit in a future video.
André
Hey André, I would suggest adding this to the description of the video.
Hi, firstly love what you've done with the tutorial. But for some friendly feedback, already after changing the panels, opening a new airfoil, where is this tech winder folder with all the airfoils files? Is it included with the XFLR5 download or is it found somewhere else? On the website? A third party website? Can't find this folder. Would be good to have an explanation somewhere in the beginning about everything needed for the program. Also, it would also be good if you could say things like "let's design a naca airfoil by clicking on the design tab and clicking naca foil" or "re-panel the airfoil by clicking the design tab and clicking redefine globally" its a bit tedious having to just follow visually pausing the video and switching from the video to the program for those of us with one screen only. Again, nice job overall, just little things to make things feel more smoother.
Thank you so much for an excellent introduction to XFLR5!
Where My Riddle AE 317 homies at?
Thanks for taking the time to do these videos!!
It's all well and good for someone who is familiar with the mechanics of the program. I wonder how long it took for you to become familiar with its features and functions. Jumping about as you do so quickly is of no help to a neophyte trying to analyse a cuff for the leading edge of my plane for better STOL performance. I suppose the best answer is to get another plane.
Salut André,
Thanks for sharing your knowledge with us. It was very instructive and helpful.
All the best,
Gustavo
Thank you for this helpful video list!
Hello from Turkey!
NEED HELP..!! when i import a custom made foil from solid works, everything goes fine but when i run the analysis graph doesnt get plotted and it shows unconverged after 100 iterations but the main problem is that nothing gets plotted on the graphs.....please help...!!
usually if you just insert a graph from the coordinates the trailing edge of the airfoil is open, two lines aren't connected, so it can't run analysis on open foil
Hey, I have the same problem right now. Is there anyway I can connect the trailing edge? I did not import a foil btw. I used the design selection and made a NACA2314 . Don't know why it did not connect the trailing edge points...
I have a new question..WHY DOES XFLR5 CALCUTE Cd if panel methods don't predict viscous effects, just because it use potencial flow theory?
bro... you saved my life... thanks a lot
thanks for the explanation its was great, where can I get xflr5 document u mentioned in the video
i was waiting for playlists from a longtime. please can you give a manual of the software.
Thank u in advance !!!
Thanks you man ! I'll watch this carefully ! Salut depuis la France ! Hi from France !
In the analysis window, there are two analyses, one is alpha another one is Cl. But I could not the difference. I can just use alpha. What is analysis Cl for? In this video example also use alpha for the analysis.
Hello Sir, how can i see the graph of Cd with the analysis? Infact, for my exam i need the graph of Cd function of alpha.. How can i do.. Thanks for the answer.
Thank you very much for this great tutorial!
Is there a tutorial for the combination of different profiles eg at the root ag24 and ag25 at the end ? Which rules are there for the alignment of different profiles on which axis ? Specifically explained in the program xlfr5. Thank you for answer, Joe
Hi i've followed your tutorial but it doesn't seem to load a cp graph after clicking analyze. I'm not sure what I'm missing. Thanks
What should be the Mach number for the RC trainer aircraft...???
Hi sir!
I can't understand the differences between type 1-2-3 and 4.
I've searched about it on the internet but couldn't find any documentation.
What is the difference between types in airfoil analysis?
Can u please elaborate about XTR top and bottom, trip location and N rit...???
Can you analyze multi element airfoils with xflr5 ? (like naca 6412 airfoil with a naca 4412 flap etc) I tried to look for it on the internet but since I don't really know what I am doing at this moment, I couldn't really find anything.
It's an amazing video. But it's such a pity that I'm a Chinese, I can only understand a little. Do you have any other excellent design of electric glider? (I mean, based on XFLR5) I really need it. Thanks bro!
The only documentation I have is on the web site www.xflr5.com including some Chinese translations.
@@techwinder thank you very much
What should be the Renaulds number during xfoil direct design????
Thanks.
Hello André. For Naca 0009 analysis, panel number is 99 and there is a node at leading edge. But you re-panel the airfoil for 100 panels. After this refinement leading edge node is deleted and leading edge panel becomes perpendicular to the airflow at zero degree angle of attack. Is this good for the analysis? I mean did you do this (even number of panels) intentionally?
I don't think it has any impact. Even if it has, I couldn't say which is more representative. Did you run a comparison ?
I did not run a controlled comparison analysis for a Reynolds number range yet. But i can say that leading edge node is essential for any numerical analysis.
most the things you click are greyed out on my version ..
Why do you always use Mach number 0? For that to be true, the velocity of the plane should be 0 (or very small), shouldn't it?
You're right, but XFoil doesn't converge as well when the Mach number is non-zero. For the precision needed, I tend to find that the assumption of incompressible flow is acceptable, especially since the 3D panel analysis methods are also based on incompressible flow assumptions.
That makes sense, thanks.
Hello!
I have been trying to understand which Reynolds number we are entering at this stage (@3:50, Re = 100,000) and searched everywhere to try to understand but I can not find any information or definition for that Reynolds number. I am currently running simulations on a miniature model wind turbine (0.5m diameter) and if I base that Reynolds number on the chord length, I get an Re of about 12,000 which is very low and pretty much leads to little to no power from the turbine, and a quasi-entirely negative Cp.
Can you please help me out if you know what that Reynolds number is based on?
Hello, Sorry for the late reply.
I'm not sure I quite understand the question. If your wind turbine airfoil operates at 12k, that's the value you should set in the analysis. Re = V. Chord/Kinematic viscosity.
The fact that Cp is
downloaded v6.55 to my Mac(Monterry 12.1) but it wont open new project, just grey window with "ready" in lower left corner
Sir I am unable to access the tools in xflr 5. My kind request is to help me to resolve this issue..
Thank You !
No Cp graph appears after I click analyze. Can someone please help?
For anybody stuck on the same problem, I resolved it by using the same xflr5 version as the one used in the video (6.12)
thx
Thanks for this great playlist. I have a problem with panel viev. After I rightclick at foil there is no option to show panels. How can I make this work?
Things have changed a bit. Use the submenu CurrentFoil/setStyle, and choose an option for the points.
Hello man
How can i add another airfoil to this application?
Did you downloaded extra folders?
Please help
I need analysis airfoil for gliders
Hello Techwinder, I would like to ask for some help: how do I import a new airfoil model to XFLR5?
I need to analise a wing using the Selig 1223 foil but I cannot find it at the foil base.
Thanks!
here airfoiltools.com/airfoil/details?airfoil=s1223-il
Hey thanks so much for this great tutorials
i have an error say Warning : error reading the file Saved the valid part
i really need help
It means that the project file is corrupt. Not much can be done unfortunately.
Hate to be a noob but what are panels here and how does increasing its number help in analysis?
A Panel is the line segment between two points.The foil is approximated by this collection of line segments.
Increasing the number improves the approximation, and typically ~100 panels is enough for a good approximation.
techwinder and what is convergence?
Convergence is when an algorithm such as the one built in XFoil reaches a result within a finite number of iterations.
techwinder soo what causes unconvergence?
helooo
i need your help in this problem
when i need analyze this wing
( NACA 2412 airfoil ) Wing (Cord is 152 mm , Span 225 mm area 0.035 m^2 )
at fixed speed 30 m/s
what is the solv for this Problem pleas ((unconverged after 100 iterations out of 100
_________
Analysis completed ...some points are unconverged )))
thanks i will try it :-*
I am currently trying to use xflr5 for NACA2412 and NACALS0417 but it either doesn't converge or there is a compressibility error. I've tried following your first step in terms of the panelling but that messes up/changes the shape of the airfoil, making the analysis pretty much impossible; is there any way you can help?
There's no reason for panelling to change the shape of the airfoil. Also from my experience, it usually only improves convergence.
Compressibility errors usually arise when trying to set a non-zero Mach number. Unfortunately, I'm not familiar enough with the inner workings of xfoil, so for this error you would get more help from the xfoil forum @yahoo groups.
If you can't work it out, please share the project file and I'll have a look.
hi, is it possible to do it with airfoil sd7080
when i run analysis for cessna 172 aircraft RE 6 MILLION I HAVE ERROR I cl= 1000 at same alpha
why this error plz and what my be the error
Hi. I am having problems with installation of the file. Very new to this. I am running windows 7- 32 bit at my university. When I download the package. Do I just run the exe file? if so, when I do, xlfr5 opens but the entire file is blacked out. No menu. But if I go to the top of the program and click along the top line, the sub heading of the menu options appear. Even if a create a new, the entire program is there, its like its all there but blacked out. I tried changing the text colour.
Thanks
This sounds like an OS issue. Only advice I can give is to try to run on another computer.
My XFLR is not showing show panel option.....I am using windows 7 64 bit version 6.37.... please suggest a solution
Please upgrade to v6.43. It's always good practice to use the latest version anyway.
I had the same problem with the latest version. You may need to do what Techwinder suggested in a reply to another comment. He said "Use the submenu CurrentFoil/setStyle, and choose an option for the points."
Which air foil do you recommend? I try to make a wing kind.
That's a very general question. The choice depends on what kind of flight you are targeting.
Besides, I don't really want to give advice. The purpose of xflr5 is precisely to help you make your own design choices.
Ok, I just want to take pictures ir order to find the NDVI index. The flight most be gentile.
In my laptop 3d view is not start why
can you please help me with the step by step process of installing the XFLR5 software?
Its really urgent...thanks in advance!
Download. Unpack. Double-click. Done.
it shows "The application was unable to start correctly (0xc000007b). Click OK to close the application."
I have tried many things, but nothing is working...pls suggest what can be done.
Thanks for ur reply.
tried that also but doesn't seem to be working :(
Don't know... are you running a 64 bit OS?
that's rite
What is cm here?
Hello,
It is not possible to download the project file used in this Demo.
Can you upload it or send it to me by e-mail?
Thank you
I've restored the link
I am using a Mac with OS X 10.11 and I cannot get a .dat file. XFLR5 will not open .txt files. Any ideas, please??
+jdomnhl17 I run 10.10.5 and have no problem. What exactly is the problem? You could try doing "Get Info" on the dat file (right click/command click) then "Open With", and select XFLR5 as the app to open it with.
+Hans Conser I figured out that when downloading the file from the airfoil database, Safari was saving it as a .txt file named "XXXX.dat." So that was the problem. I just switched to Chrome :)
Can we know the Cd0 Cl0 Cm0 informations using that tool, how can I reach these datas
Sure, you can read them on the graphs.
@@techwinder where are there I couldn't find them anywhere, I have a study teacher ask for me these datas, do you have any VIDEO or SOURCE about these Cm0, Cl0....??? Could you share the link or address??
@@BA-ix4my Just plot the graphs Cl=f(alpha) and Cm=f(alpha) and pick the values for alpha=0
@@techwinder thanks you helped me so much , I have just one more question at cruise my Mach number is 0.8 should I write as 0.8 because most of the case it is written 0?????
@@BA-ix4my yes, but note that xfoil does not converge well with non-zero Mach numbers, at least in its implementation in xflr5
i wanna design Htol or vtol both function aircraft is it posible in XFLR ?
No, neither the LLT nor the panel methods are adapted to the air flows of these kind of flights
papi vergatario