Unformatted text preview: 0.2c and which is deflected 25 degrees.(ie the rear 0.2c of the camber line is deflected downwards – account for the change in chord and recall the chord line connects the LE and TE) When the geometric angle of attack is 4 degrees, what is the section lift coefficient? Where is the center of pressure?...
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- Spring '07
- Airfoil, NACA, 4 degrees, symmetric airfoil, 25 degrees, 1.5 degrees