Question

An NACA 2412 airfoil has a mean camber line defined as: (y/c)fore = 0.125[0.8(x/c) - (x/c)²] (y/c)aft = 0.0555[0.2 + 0.8(x/c) - (x/c)²] where fore indicates forward of the maximum camber position and aft indicates behind. Using thin airfoil theory, find the following: a. Cl(?) b. Cl? c. Angle of attack at zero lift (?L=0) d. Cmc/4 e. CmLE

          An NACA 2412 airfoil has a mean camber line defined as:
(y/c)fore = 0.125[0.8(x/c) - (x/c)²]
(y/c)aft = 0.0555[0.2 + 0.8(x/c) - (x/c)²]
where fore indicates forward of the maximum camber position and aft indicates behind. Using thin airfoil theory, find the following:
a. Cl(?)
b. Cl?
c. Angle of attack at zero lift (?L=0)
d. Cmc/4
e. CmLE

An NACA 2412 airfoil has a mean camber line defined as:
(y/c)fore = 0.125[0.8(x/c) - (x/c)²]
(y/c)aft = 0.0555[0.2 + 0.8(x/c) - (x/c)²]
where fore indicates forward of the maximum camber position and aft indicates behind. Using thin airfoil theory, find the following:
a. Cl(?)
b. Cl?
c. Angle of attack at zero lift (?L=0)
d. Cmc/4
e. CmLE

Added by Juan Antonio P.

University Physics with Modern Physics

Hugh D. Young 14th Edition

Instant Answer

Solved by Expert Adi S

07/12/2023

Step 1

125 \left( \frac{x}{c} \right) - \left( \frac{x}{c} \right)^2 \) - Aft of maximum camber: \( \frac{y}{c} = 0.0555 \left[ 0.2 + 0.8 \left( \frac{x}{c} \right) - \left( \frac{x}{c} \right)^2 \right] \) Show more…

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An NACA 2412 airfoil has a mean camber line defined as: where fore indicates forward of the maximum camber position and aft indicates behind. Using thin airfoil theory, find the following: a. Ci(α) b. Clα c. Angle of attack at zero lift (αL=0) d. Cmc/4 e. CmLE