Lift generated by a blade is proportional to the
- relative airflow and the angle of attack.
- relative airflow and the pitch.
- aircraft airspeed and angle of attack.
Explanation
Blade lift rises with the square of the relative airflow (the velocity actually seen by the blade) and with the angle of attack up to the stall. Aircraft airspeed alone is not the relevant velocity for a rotor, and pitch angle only sets lift indirectly through the resulting angle of attack.
gcshukla9 asking:
lift generated by a blade is proportional to relative airflow & the airspeed as mentioned in this question.
Can anybody throw light on this ?
Community Comments (4)
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dimky Posts: 514 22.02.2014 / 18:26
If aircraft airspeed is 0, blade can't produce lift? :)
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gcshukla9 Posts: 3 22.02.2014 / 19:18
with aircraft speed zero (at hover) helicopter still can produce lift, hence the lift is proportional to relative airflow & not the aircraft speed
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dimky Posts: 514 22.02.2014 / 22:43
Uhu
J
Jordi Posts: 198 01.09.2021 / 11:15
i think the correct is relative airflow and angle of attack because at hover the a/c doesnt move so we dont use "aircraft speed" but we still hover and have lift.Also if we change the angle of attack of the blade so does the lift .So Lift changes with relative airflow and AOA .Also i have a pdf with questions and this question is 2 times with different answers.1 answer is this and the other has correct with aircraft speed.But for me this answer is the best.
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