1. a http://www.pagendarm.de/trapp/programming/java/profiles/NACA4.html
Angle of attack
Middle line
Velocity
Cord

2. c
Lift FL
Drag FD

3. Pressure distribution around an airfoil-
Pressure along the upper surface DH +
Pressure along the lower surface

4. Lift
Lift FL

5. Lift coefficient CL FL

6. Drag
Drag FD

7. Drag coefficient CD FD

8. Blade profile data Angle of attack d v Angle of attack
Average relative
velocity

9. Peripheral velocity = w Wind velocity = C Relative velocity = V V C U

10. U V
Torque
Trust C FL FD

11. U V C
Torque
Trust U V
Torque C
Trust

12. C
Fthrust
Torque
Trust
M’torque w
F’thrust
M’thrust