Talk:Transverse flow effect

In forward flight, air passing through the rear portion of the rotor disk has a greater downwash angle than air passing through the forward portion

The downward flow at the rear of the rotor disk causes a reduced angle of attack, resulting in less lift. Increased angle of attack and more lift is produced at the front portion of the disk because airflow is more horizontal. These differences between the fore and aft parts of the rotor disk are called transverse flow effect. They cause unequal drag in the fore and aft parts of the disk resulting in vibrations that are easily recognizable by the pilot. The vibrations are more noticeable for most helicopters between 10 and 20 knots.

The assertion that the effect is not due to gyroscopic procession is not necessarily accurate - I'm not confident enough to remove it, but blade flexibility making the angle not precisely 90 degrees doesn't mean the effect isn't present at all! You're still inducing a couple on a rotating body. It definitely needs a citation, and may well be inaccurate. — Preceding unsigned comment added by 131.111.5.173 (talk) 15:23, 14 May 2022 (UTC)