Hi, I am attempting to analyze an Formula 1 rear wing, the camber is negative, and I have assigned the chord and the span. I have tried a type 1 analysis with a fixed free stream speed, but can' get it to converge nor to interpolate. At the end of the analysis the message "errors encountered" appears. Could you help me please? Am I doing something wrong?
I did an analysis using type 1, for different velocity. Why the streamline for different velocity looks the same. The lift show different but streamline always the same no matter the velocity value. Can you explain why the streamline all the same,?
I tried doing this analysis several times by now.. unfortunately i cant find any graphs and the log tells me the interpolation failed at every single span Position
Hello. I try to design B747-200 and analyze it, but I have several problems: 1- It's recommend not to design fuselage. Should we consider fuselage's mass and inertia? How should I do it? 2- For stability analysis we should locate X_CG and to do that we need mass and inertia. How should we define them? 3- For stability analysis (Type 7) we need to define mass and inertia. How should I do that? Could you please give me a hand? Wating for your feedback.
Hello, again! I designed a small aircraft on XFLR5, and then I tried to analyze it, but when it starts to compute the on-body speeds, it says "could not be interpolated" for all the angles. I didn't set the plane inertia, but I filled the mass and CoG while defining the analysis. Do you have any idea of what could have happened?
I watched your 11th tutorial and found the problem, I forgot to batch analysis for the profiles of the elevator and the rudder. Everything is working properly now. Thanks!
Hello techwinder I'm using your program for a DR-400 aircraft. I've design the wing and I'm trying to do an analysis ... The analyse is : Type 2 (fixed lift) with ring vortex (VLM2) and i'm using the plane inertia define with the plane. But my probleme is that when I launch the analyze errors appeared for exemple "could not be interpolated" or "outside the flight envelope"... Did I made a mistake in the Analyze ? Can you help me please ? Waiting your feedback ... ;)
Hello, great tutorials. I have just one problem: when I run the analysis for the plane I get this error on every point *Span pos = 0.17 m, Re = 970455, Cl = 0.91 is outside the flight envelope* and hence it doesn't generate any graphs at all. Any advice? edit: alternatively I also get this one *Cl could not be interpolated*
All right, will do it in a future update. In the meantime, there are two ways to do this : either set a 90° dihedral at the tip panels of the wings, or use the double fin option with a positive y value. I used the first method for the flying wing in the sample project, which is available for download on the project page in the files section.
Nice video ¡¡¡...You helped me a lot but a have an error like this: Calculating wing...Fin Span pos = -60.00 mm, Re = 34 000, Cl = 0.00 is outside the flight envelope Span pos = -34.62 mm, Re = 36 000, Cl = 0.00 is outside the flight envelope Span pos = -14.27 mm, Re = 40 000, Cl = 0.00 is outside the flight envelope Span pos = 2.97 mm, Re = 45 000, Cl = 0.00 is outside the flight envelope Span pos = 14.27 mm, Re = 49 000, Cl = 0.00 is outside the flight envelope Span pos = 34.62 mm, Re = 53 000, Cl = 0.00 is outside the flight envelope Span pos = 60.00 mm, Re = 55 000, Cl = 0.00 is outside the flight envelope Panel Analysis completed ... Errors encountered Can you help me to fix this? ..Greetings from Ecuador.. God bles you jaja
![[#2024MAMA] G-DRAGON - 무제(Untitled, 2014)+POWER+HOME SWEET HOME+뱅뱅뱅+FANTASTIC BABY | Mnet 241123 방송](http://i.ytimg.com/vi/Ox29z5Nf1Uk/mqdefault.jpg)
Great tutorials! Is it possible to set the parameters to simulate water as the fluid as well?
Hi, I am attempting to analyze an Formula 1 rear wing, the camber is negative, and I have assigned the chord and the span. I have tried a type 1 analysis with a fixed free stream speed, but can' get it to converge nor to interpolate. At the end of the analysis the message "errors encountered" appears. Could you help me please? Am I doing something wrong?
I did an analysis using type 1, for different velocity. Why the streamline for different velocity looks the same. The lift show different but streamline always the same no matter the velocity value. Can you explain why the streamline all the same,?
andre, i can only save analysis, where can I go and run the analysis for the plane?
Did you open File --> Wing and Plane Design first? When this is activated, there should be a little model of a plane in the toolbar like in the video.
I tried doing this analysis several times by now.. unfortunately i cant find any graphs and the log tells me the interpolation failed at every single span Position
Hello. I try to design B747-200 and analyze it, but I have several problems:
1- It's recommend not to design fuselage. Should we consider fuselage's mass and inertia? How should I do it?
2- For stability analysis we should locate X_CG and to do that we need mass and inertia. How should we define them?
3- For stability analysis (Type 7) we need to define mass and inertia. How should I do that?
Could you please give me a hand?
Wating for your feedback.
thank you very much sir I applied the same method of 90 degrees dihedral and getting amazing results with lessened vortex drag
how can i edit the analysis after create analysis?
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?
Hi, i have problem with the software. Curves doesn't exist after i click analyze, and i can't click any results. Can you help me?
Hello, again! I designed a small aircraft on XFLR5, and then I tried to analyze it, but when it starts to compute the on-body speeds, it says "could not be interpolated" for all the angles. I didn't set the plane inertia, but I filled the mass and CoG while defining the analysis. Do you have any idea of what could have happened?
I watched your 11th tutorial and found the problem, I forgot to batch analysis for the profiles of the elevator and the rudder. Everything is working properly now. Thanks!
Please check the video 11 "plane viscous analysis errors"
Very useful videos thanks for uploading them! Is it possible to use other tail configurations? for example a V inverted tail
Sure, disable the fin, and set the dihedral angle in the elevator definition
And how It Is possibile to design a triple tail? Imposing the dihedral to 90 degree gives me some issues. Thank you!
Hello techwinder I'm using your program for a DR-400 aircraft.
I've design the wing and I'm trying to do an analysis ...
The analyse is : Type 2 (fixed lift) with ring vortex (VLM2) and i'm using the plane inertia define with the plane.
But my probleme is that when I launch the analyze errors appeared for exemple "could not be interpolated" or "outside the flight envelope"...
Did I made a mistake in the Analyze ? Can you help me please ?
Waiting your feedback ... ;)
The explanation is in video 11 th-cam.com/video/_8thw2CQCaI/w-d-xo.html
I am unable to select an airfoil from the drop down menu. Do you mind letting me know what's wrong?
Nvm. I just found out that you had to load an airfoil for it to appear in the drop-down menu.
Did you load the foils in the first place? Are you sure they weren't deleted inadvertently?
Hello, great tutorials. I have just one problem: when I run the analysis for the plane I get this error on every point
*Span pos = 0.17 m, Re = 970455, Cl = 0.91 is outside the flight envelope*
and hence it doesn't generate any graphs at all. Any advice?
edit: alternatively I also get this one
*Cl could not be interpolated*
The answer is in video 11 th-cam.com/video/_8thw2CQCaI/w-d-xo.html
INSERTING WINGLETS IN PLANE WING
Sir I am a RC plane enthusiast can you please upload a video Regarding adding the Winglets in the planform of wing
All right, will do it in a future update.
In the meantime, there are two ways to do this : either set a 90° dihedral at the tip panels of the wings, or use the double fin option with a positive y value. I used the first method for the flying wing in the sample project, which is available for download on the project page in the files section.
Nice video ¡¡¡...You helped me a lot but a have an error like this:
Calculating wing...Fin
Span pos = -60.00 mm, Re = 34 000, Cl = 0.00 is outside the flight envelope
Span pos = -34.62 mm, Re = 36 000, Cl = 0.00 is outside the flight envelope
Span pos = -14.27 mm, Re = 40 000, Cl = 0.00 is outside the flight envelope
Span pos = 2.97 mm, Re = 45 000, Cl = 0.00 is outside the flight envelope
Span pos = 14.27 mm, Re = 49 000, Cl = 0.00 is outside the flight envelope
Span pos = 34.62 mm, Re = 53 000, Cl = 0.00 is outside the flight envelope
Span pos = 60.00 mm, Re = 55 000, Cl = 0.00 is outside the flight envelope
Panel Analysis completed ... Errors encountered
Can you help me to fix this? ..Greetings from Ecuador.. God bles you jaja
Please check the video 11 "plane viscous analysis errors"
Salut salut! Pourriez vous faire des tutos en français?
OK, peut-être mais pas tout de suite.
Hello techeinder. Your videos are very amazing.I am a prablem to analysis plane in xflr5.please give me your email ?