Chapter 5: Airfoil Pressure Distribution Flashcards
1
Q
Pressure Distribution Dependence (4)
A
AoA
Camber
Thickness
Airflow velocity (changes magnitude only)
2
Q
Symmetric Airfoil
CP / Stagnation point change?
A
CP doesn’t move with AoA (25% chord)
Stagnation Point at LE but goes down with AoA
3
Q
Camber Airfoil
CP / Stagnation point change?
A
CP moves forward with AoA ( 23 - 27% chord)
Stagnation Point at LE but goes down with AoA
Produces lift at AoA = 0
4
Q
Coefficient of Lift
A
Surface Pressure / Dynamic Pressure