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No Cp graph appears after I click analyze. Can someone please help?

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 !

thanks for the explanation its was great, where can I get xflr5 document u mentioned in the video

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,?

Thanks! My aerodynamics teacher, whose name resembles a typical vacation place here in Spain would have been very mad at me if it wasn't for you. This tutorial is the winning design.

Hello, great work with flow5! Is there a way to read xfoil polars? Since Xflr5 is not scriptable, I was thinking about running a 2D analysis on xfoil and using those polars to run the scripted 3D analysis on flow5, is that a possible option? Xfoil exports polars in txt files, how can I load those in Flow5? Thank you for the help.

Is it possible to design invented boom mounted ni xflr 5?

Can you analyze a split flap?

Great explanation, thank you, god bless you

Hi, I just have a couple of questions! What is the Vinf (speed to balance the weight)? What if the Vinf is not located on a curve? Is it okay to run this static analysis with the plane set at a certain velocity? Also, do you know why following the static analysis, only one point is plotted?

Nice presentation, thanks Andre

What can you tell about this softwsre now. Can it be use for general costruction of plane now ?

Great

Hi! Techwinder, I just wanna say thank you for all of your works 😁. It is really helpful ❤.

If I keep the fuselage width, length and height coordinates, how can I add them to xflr5? I have tried to modify the body and the fuselage is deformed and I tried to get coordinates of a sailplane similar to the one I simulate to import them into the software and I couldn't find them.

great job and great tutorial!

techwinder, I believe the General Licence for xfoil allows for the sale of "wrapper" programs that build off of xfoil as in that agreement it is acknowledged that creators may still be compensated for their own contributions. If not, is there any way to work around the licensing by simply allowing a "drag and drop" folder where xfoil may be downloaded externally by the end user and combined to provide that functionality? I suppose its not so big of a problem to run xflr5 and flow5 separately and transfer data. I'm a longtime user of xflr, about to give Flow5 a try once I have a new aero project in mind.

Hi, the dutch roll mode for my plane falls on the right side, but it has no imaginery value. On the 3D view, the plane just veers towards the negative y axis continuously

Hey! Could you please drop down your email as I have a few doubts that I want to clear with this software. One of the main ones being why does the software not analyze for the whole range of angle of attacks sometimes

hi, is it possible to do it with airfoil sd7080

Hello man How can i add another airfoil to this application? Did you downloaded extra folders? Please help I need analysis airfoil for gliders

How to change the aoa for a given Cl ?

Hi so, for my physics project, I decided to find the effect of dihedral angle on the longitudinal stability of the aircraft, and I decided to go with NACA 0012. I found that when the dihedral angle is 0 degrees, the neutral point was somewhere about 0.0442 m away from the leading edge, whereas the CoG was at -2.034 m away from the leading edge (meaning its in the opposite direction and its 2.034 m from the wing). This was the point when XFLR5 gave a line that made a 45 degree angle between the axes. 45 degree was taken in as the angle, since this was the angle that would make the wing not too stable (too jerky of a ride) and not too unstable. The MAC of the wing was 0.180 m (from XFLR5) and the static margin that I computed (I was shocked) was 11.5455555556 or (11545.5 %). I don't know what I did wrong.

Sir, do you have the solidworks model of the aircraft,if you have can you please share

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.

How can ve solve if we have two error in same reynolds

While doing stability analysis on xflr5 I'm facing some errors that's why the modes for longitudinal and lateral stability are not operating could you plz guide me through this?

how do populate the re number list automatically?

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

Thank you this is really helpful

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?

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?

Hello. It when saving changes to a sail, it requires i set reference dimensions. What do those represent?

Does the version Different the convergent of airfoil Calculations hope answer

what is the Cm?

hi, the lines on the graph are all the same color. how to set different color assignment for each drawing

Hi, is there a way to make the flap tilt in the analysis instead of the whole foil tilting?

Answered my "Interference" question here. What about Fuselage pressure distribution and turbulent/laminar flow drag reduction?

Does Flow5 generate 3D pressure distributions, with details around intersections? E.g. will it add wing and fuselage pressure distributions together at the wing joint, and model interference drag? And will it predict Laminar v.s. Turbulent flow/drag on fuselage surfaces? Thanks!

Brilliant!

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.

Merci encore ! :)

Encore un gigantesque merci pour cet outil et toutes ces infos ! MERCIII ! ;)

you shouldve made this tutorial the same way as the xflr5 one

@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.

You are doing an amazing work, thank you so SO much for all this! Merci !

Hi. Thank you for this insightful demo. I have used your 'foil_script.xml' file to automate my XFLR5 runs. However, I would like to know what the foil_analysis.xml input file looks like? I have generated one using XFLR5 export but unfortunately it is unreadable by the program. Could you perhaps share a link where we could download the scripting files you have used in this demo so that we may get an idea of what the contents of the file are and subsequently edit it for our own analyses. Thank You.

Thank you so much for these videos!

First thanks for the great tutos, they help a lot. when i change to xfoil inverse Design they just give the foil with the flap and i cant change it ? Even if i put the selected Foil in Oppoints and polar view it gets changed. Could you help me please