Aircraft Performance . Thrust Required . Derivation

[@aryans.m5746]

first of all, very accurate, simple, and smooth teaching. this videos was life saving at least for me. home to see more. but would be great if we can have the teaching fills is there way for that?

[@indepviewpt]

Thank you for this video.

[@techknow8195]

Considering the orientation of the wing, I think the lift should have been perpendicular to the chord line of the wing. So the weight should have made an angle we the lift line extended

[@AeroAcademyOnline]

Lift is defined as perpendicular to the direction of the freestream velocity. It actually is not defined relative to the aircraft, but rather relative to the direction of the freestream velocity. So lift is not always perpendicular to the chord line of the wing.

[@malengineer]

Hi, there is an issue with that definition of angle of attack. The angle of attack is the angle between the chord line and the relative wind/airflow.

[@Dannyp010]

A little late but i thought it was wrong as well, but by looking a bit further on the internet. Is it correct that the AoA doesnt necessarily have to be with the chord line of the wing as a reference (to the relative incoming airflow) but can also be taking from a different reference line on the airplane/wing (to the relative incoming airflow)?

[@SunilSundar]

Thanks for this. Is there a way to calculate the thrust developed by an engine with a known power output? Thanks again

[@Bigboyjingles]

To simply all this, why can't we just use trigonometry to calculate the magnitude of the hypotenuse (thrust force) using the required lift force (weight) and the angle of attack?