sagar vijay thik

hello there, I am performing stability analysis on UAV , and it is not stable in spiral mode, what should I do to solve this problem ? Please find attached root locus plot for lateral case.

hello there, I am performing stability analysis on UAV , and it is not stable in spiral mode, what should I do to solve this problem ?

I created rectangular wing with inverted v tail configuration and add mass to the wing and tail are 5 and 2 kg respectively, and after doing analysis it shows positive slope of cm vs alpha and yes it is unstable condition . I ran Similar analysis by not giving any masses then it shows stable cm vs alpha curve. please help me with this issue. Please find screenshots of design of main wing and tail

I created rectangular wing with inverted v tail configuration and add mass to the wing and tail are 5 and 2 kg respectively, and after doing analysis it shows positive slope of cm vs alpha and yes it is unstable condition . I ran Similar analysis by not giving any masses then it shows stable cm vs alpha curve. please help me with this issue. Please find screenshots of design of main wing and tail

OKay so as i Understood u selected an airfoil and picked up value at 4 deg AOA ,but that analyis u might have done for airfoil (2-D) section, but when u anlysing results for 3D wing then results changes bcoz of losses & 3D effects. So I would suggest first decide wing area by performing Constraint analysis, u will directly get wing area if u know the weight.

i'm currecntly using v6.48 version of xflr5 software .I tried to design a flap for a wing,for that i divided wing into 3 sections. I need to give flap deflection for mid section , for doing that i set flap for that sepecific airfoil in direct foil design. And when i update that airfoil in 3D plane then whole trailing edge is converted into flap, but i set flap for ony that mid section airfoil? please see attached image file below.

i did design a tapered wing and used ring vortex[VLM2] method . and i got lift distribution at negative AOA, which is weird it left the main wing body as you can see in the attached image, please someone explain me where I went wrong?

I did that, but it's not working , it's taking 1e7 ,1e8....and so on but it is not accepting 1e6 range On Wed, Mar 31, 2021, 07:48 "André" techwinder@users.sourceforge.net wrote: Just type in 1e6? reynolds number greater than 900,000 https://sourceforge.net/p/xflr5/discussion/679396/thread/c31e8a6861/?limit=25#2cd7 Sent from sourceforge.net because you indicated interest in https://sourceforge.net/p/xflr5/discussion/679396/ To unsubscribe from further messages, please visit https://sourceforge.n...