Chapter 5: Airfoil Pressure Distribution Flashcards

1
Q

Pressure Distribution Dependence (4)

A

AoA
Camber
Thickness
Airflow velocity (changes magnitude only)

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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

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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

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4
Q

Coefficient of Lift

A

Surface Pressure / Dynamic Pressure

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