A NACA 22104 airfoil is operating at AOA = 3°. The lift-coefficient at this AOA is 0.15. Determine the value of angle of attack at designed lift co-efficient.
A NACA 22104 airfoil is operating at AOA = 3°. The lift-coefficient at this AOA is 0.15. Determine the value of angle of attack at designed lift co-efficient. Correct Answer 4.36°
Given NACA 22104 airfoil. AOA = 3°, Cl = 0.15 at 3° Based on NACA -5 digit series design Cl = first digit*0.15 = 2*0.15 = 0.3 Now, for thin airfoil lift curve slope = 0.11 per degree 0.11 = (design Cl – Cl at 3°) / (AOA –3°) 0.11 = (0.3-0.15) / (AOA -3°) 0.11*(AOA -3°) = 0.15 Hence, at designed Cl, AOA = (0.15/0.11) + 3° = 4.36°.
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Feb 20, 2025