Hello, I want to analyze a v tail aircraft. Should I just give a 36 degree dihedral to the elevator and ignore the fin or is there another way of doing it properly? Thanks for the information
Dear Techwinder, How are you setting up the dimensions of nose lead and battery on x axis r u referring some plans that you have already made it or it's random if planned do tell us how did we dimension the length of the wing/elevator/fins...etc
i encounter the ''Found a negative lift for Alpha=-9.53740.... skipping the angle...'' problem, so i cannot run stability analysis, How can i fix that ?
I have a doubt that whether Xflr5 use formula for taper ratio = Cr/Ct as we can see in the video that taper ratio is greater than 1...normally taper ratio is Ct/Cr .Please help me.
The idea would be to use Type 2 polars. These polars adjust the velocity so that the lift force, which is proportional to wing area, balances the weight. So if you know at what speed you intend to fly this plane, you'll be able to tell if there is enough wing area.
when I go to add an airfoil to a section of my wing, there are no airfoils I can select from in the "Define Wing" window. How do I add airfoils to make my wing 3D? Thank you
Got a question, in minute 2.20 you increase the dihedral angle on the outside part, so, this angle is measured by adding the last dihedral angle (1° for the first part), making it a 3.5°? or it's just by itself 2.5° in relationship with the horizontal axis?
excellent videos. could you plss make a video on possible errors that might occur while defining and analyzing any part of the plane and methods to correct it. eg "panel sequence is inconsistent" .
"Panel sequence is inconsistent" means that the foil sections are not defined from root to tip along the span, i.e. at least one section has span position < than the next one.
In here u defined mass of servos twice, once while defining inertia of the wing and second while defining overall weight along with nose weight.... why is that??
Sorry, I got a question. I've done the same as you do in your tutorial, but when I define the wing mass, 0,300g, my X_CoG, Z_CoG, and also moments of inertia, are different from yours. I've checked it and done it 3 times but they are still different. For example, Your X_CoG is 79.737 and mine is 80,874, and your Z_CoG is 9,404 and mine is 10,694. In Z_CoG theres a difference of 13,7%.... If I've done the same as you did, do you know what could be the problem or what should I check? I've already checked the wing dimensions (wing span, area, projected span and area, mean geom. chord, mean aero chord, aspect ratio, etc.). Im also working on the latest version, V6.12 thanks in advance.
+techwinder thanks for the file. I've checked it and the xcog and zcog are the same as I got. At minute seven it appears the values I wrote above, but in your file they are the ones I got, so problem solved. Thank you. Your videos helped me a lot.
Thanks for these great tutorials Andre. I loved the part at 3:12 where you were unhappy with the colour of the wing - I feel exactly the same way.
ALLAH BELANI VERSİB
Hello, I want to analyze a v tail aircraft. Should I just give a 36 degree dihedral to the elevator and ignore the fin or is there another way of doing it properly? Thanks for the information
How to draw a body and convert it to an xml file? to export into XFLR5
This body can not draw with xflr5.
Thanks for your help!
Dear Techwinder,
How are you setting up the dimensions of nose lead and battery on x axis r u referring some plans that you have already made it or it's random if planned do tell us how did we dimension the length of the wing/elevator/fins...etc
Hello, can we analyze something like subsonic airplanes using xflr 5?
Is it possible to design invented boom mounted ni xflr 5?
i encounter the ''Found a negative lift for Alpha=-9.53740.... skipping the angle...'' problem, so i cannot run stability analysis, How can i fix that ?
is it possible to give the inertia first and then decide the distance of the wing from the elevator....???
Sure. The masses of each component are defined in their own system of axis.
I have a doubt that whether Xflr5 use formula for taper ratio = Cr/Ct as we can see in the video that taper ratio is greater than 1...normally taper ratio is Ct/Cr .Please help me.
why is the tail volume a dimensionless quantity
Is it possible to define more lifting surfaces than predetermined? I mean, for example 3 fins, triplanes or both front and back fins.
No, the design is limited to 4 wings altogether
Neither modifying geometry code?
Not sure what you mean by that
subscribing..thanks for the tutorial..how to know if my wing area is sufficient enough for a given load?thanks
The idea would be to use Type 2 polars. These polars adjust the velocity so that the lift force, which is proportional to wing area, balances the weight. So if you know at what speed you intend to fly this plane, you'll be able to tell if there is enough wing area.
when I go to add an airfoil to a section of my wing, there are no airfoils I can select from in the "Define Wing" window. How do I add airfoils to make my wing 3D? Thank you
You probably don't have a foil in the "Direct Foil Design" so it won't show anything when you wanna do any analysis/design
Got a question, in minute 2.20 you increase the dihedral angle on the outside part, so, this angle is measured by adding the last dihedral angle (1° for the first part), making it a 3.5°? or it's just by itself 2.5° in relationship with the horizontal axis?
All dihedral angles are defined with respect to the horizontal axis.
excellent videos. could you plss make a video on possible errors that might occur while defining and analyzing any part of the plane and methods to correct it. eg "panel sequence is inconsistent" .
"Panel sequence is inconsistent" means that the foil sections are not defined from root to tip along the span, i.e. at least one section has span position < than the next one.
In here u defined mass of servos twice, once while defining inertia of the wing and second while defining overall weight along with nose weight.... why is that??
Well, a servo in each wing for the ailerons, and two servos in the fuselage for the elevator and rudder.
ohh ok , thnx.
thanks brother...
Sorry, I got a question.
I've done the same as you do in your tutorial, but when I define the wing mass, 0,300g, my X_CoG, Z_CoG, and also moments of inertia, are different from yours. I've checked it and done it 3 times but they are still different. For example, Your X_CoG is 79.737 and mine is 80,874, and your Z_CoG is 9,404 and mine is 10,694. In Z_CoG theres a difference of 13,7%.... If I've done the same as you did, do you know what could be the problem or what should I check? I've already checked the wing dimensions (wing span, area, projected span and area, mean geom. chord, mean aero chord, aspect ratio, etc.). Im also working on the latest version, V6.12
thanks in advance.
Maybe it should be 300g and not 0,300g ?
If it can help, I've uploaded the project for this video here: www.xflr5.com/docs/test.xfl
+techwinder thanks for the file. I've checked it and the xcog and zcog are the same as I got. At minute seven it appears the values I wrote above, but in your file they are the ones I got, so problem solved.
Thank you. Your videos helped me a lot.