Chapter 5: Airfoil Pressure Distribution

Question 1

Pressure Distribution Dependence (4)

Answer 1

AoA
Camber
Thickness
Airflow velocity (changes magnitude only)

Question 2

Symmetric Airfoil

CP / Stagnation point change?

Answer 2

CP doesn’t move with AoA (25% chord)

Stagnation Point at LE but goes down with AoA

Question 3

Camber Airfoil

CP / Stagnation point change?

Answer 3

CP moves forward with AoA ( 23 - 27% chord)
Stagnation Point at LE but goes down with AoA
Produces lift at AoA = 0

Question 4

Coefficient of Lift

Answer 4

Surface Pressure / Dynamic Pressure