1. Compressor Airfoils Example 1: 10C4/30P40 Example 2: NACA 65-[12]10
C4 type airfoil
t/c=10%
Turning or camber==2-1=30o
P=parabolic camber line
a/c=max thickness / chord=40%
Example 2: NACA 65-[12]10
65 series airfoil; 5 means 0.5c=minimum pressure location
12  CL=1.2

3. Airfoil Sections – Abbott & Von Doenhoff
NACA 4 digit airfoils
Examples
NACA 2415: 2% camber, max camber at 0.4c, tm/c=12%
NACA 0012: 0 camber, t/c=12%

5. NACA0012 Airfoil Data CL CD

6. Supercritical Wing - CDA

7. Area Rule – Coke Bottle Effect

8. Winglets