dwreck
Active Member
Hi all,
This is probably a silly question, so please bear with me. Regarding the torsional load calculation along the span of a wing; by dividing the wing into several sections/stations, one typically computes the local torsion (at one station) about a spar by the product of lift at that section and the distance between the spar and the center of pressure (roughly 25% chord for subsonic). Now let's say I place my spar at 25% chord, then by this method it means that the local torsion will be zero.
Or should I assume that my CP will be moving for changing AOA, hence use something a bit more than 25% chord?
This is probably a silly question, so please bear with me. Regarding the torsional load calculation along the span of a wing; by dividing the wing into several sections/stations, one typically computes the local torsion (at one station) about a spar by the product of lift at that section and the distance between the spar and the center of pressure (roughly 25% chord for subsonic). Now let's say I place my spar at 25% chord, then by this method it means that the local torsion will be zero.
Or should I assume that my CP will be moving for changing AOA, hence use something a bit more than 25% chord?
