Hiroshi Takeuchi asked 9 months ago
Hi,
I’m trying to leverage spanwise oppoints output numbers to structual analysis of wing. Basically, I’m going to use aerodynamic coefficients such as Cl and Cdx in order to calculate loads. However, I found there are uncertain but possible usable numbers for instance Vd.x ,y, z and F.x , y, z. Are there any description or explanation for these numbers ? In addition, I’d like to confirm that if CP.x(%) is the location of center of pressure using percentage against the wing chord at the station or not.
Regards,
Hiroshi
Main Wing
y(m) Re Ai Cd_i Cd_v Cl CP.x(%) Trans.top Trans.bot Cm_i Cm_v Bending.mom Vd.x Vd.y Vd.z F.x F.y F.z
-16.950000 133257.777027 -1.559368 0.009003 0.015059 0.330708 0.392781 0.814491 0.990264 -0.044319 0.143337 0.000000 0.000000 -0.074104 -0.191920 -0.017404 0.112491 0.284553
Hello,
The output is not documented unfortunately.
Vd is the downwash in the body reference frame.
I confirm that CP.x(%) is a percentage of the chord at the local span station.
André
André
Thank you for the confirmation. Can you let me know what are F.x, F.y and F.z as well ?
Hiroshi
They are the components of the force acting on the strip.
André