Coefficient of lift question
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Joined: Dec 2013
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From: Baleares
Coefficient of lift question
Just doing test exams and came across this one. I have put the correct answer below. I don't understand what CL0 is but assume it is a state of the Coefficient of lift ? Would love an explanation. Thanks!
Q:With respect to angle of attack:
A: CL0 occurs with respect to the difference of the true wind and the chord.
This is how CLO is written:
Q:With respect to angle of attack:
A: CL0 occurs with respect to the difference of the true wind and the chord.
This is how CLO is written:
Joined: Jun 2011
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From: england
Cl = Clo + (Cla * alpha)
where:
Cl = coefficient of lift
Clo = coefficient of lift at zero angle of attack
Cla = lift curve slope (the slope of Cl versus alpha)
alpha = angle of attack
From the lift formula Cl = L/(0.5*rho*V^2*S), the only two variables for a certain value of Cl at 0 alpha (producing a certain L) are V and S. Where S depends on the chord and V on the true wind over the airfoil.
where:
Cl = coefficient of lift
Clo = coefficient of lift at zero angle of attack
Cla = lift curve slope (the slope of Cl versus alpha)
alpha = angle of attack
From the lift formula Cl = L/(0.5*rho*V^2*S), the only two variables for a certain value of Cl at 0 alpha (producing a certain L) are V and S. Where S depends on the chord and V on the true wind over the airfoil.
