Uday Chandra G

Hello, I have a queary regarding the axis system used for computing different aerodynamic parameters in XFLR5. I came across different sources which point a varying opinion namely, Source 1:- XFLR5 Guidelines document Source 2:- Sourceforge XFLR5 discussion heading - 'Reference frame of Lift, Drag and SideForce coefficients - under sideslip' Source 3:- XFLR5 results vs Prediction document (Refer attachment for image) -> Source 1 & 2 convey that all the aerodynamic coefficients (CL, CD, Cm, Cl, Cn,...

Okay got it!

Thanks and the centre of pressure point is obtained from XFOIL right ?

Thanks. So it is the same in all cases regardless of the geomtric orientation of the wing.

Thanks. So it is the same in all cases regardless of the geomtric orientation of the wing.

Hello, I have a doubt regarding the chord-wose position of the lift distribution provided by XFLR5. 1) Is the lift distribution exactly along the quarter chord line ? (OR) 2) Is the lift distribution exactly at the centre of pressure for various sections ? The attached image visually represents the lift distribution along quarter chord line (Case 1) and the lift distribution along the centre of pressure line (case 2). ANY Insight into this would be very helpful. Thanks in advance!

What is the direction of the CL when there os a wing dihedral ? Is it perpendicular to the horizontal plane or perpendicular to the wing dihedral plane ? I have attached image that shows that the lift distribution is perpendicular to the wing. Is it a representative graphic or is the actual direction of the CL also tilted due to the wing dihedral. Any suggestions will be helpful. Thanks in advance.

I have a follow up doubt regarding this. What if I wanted to compute the resultant forces Fx, Fy and Fz over the lifting surfaces ? Do I have to utilize the Nx, Ny and Nz components ? So, Fx = 1/2.rho.S.V2.Cp.Nx Fy = 1/2.rho.S.V2.Cp.Ny Fz = 1/2.rho.S.V2.Cp.Nz where, S - wing area Is this the right approach?