Module 1 - Aerofoils Flashcards
What are distributions are used to compute aerodynamic forces and moments?
- Pressure distribution
- Shear stress distribution
To what are the normal and axial forces related?
Chord line
What is the point at the front of the chord line?
Leading edge
What is the distance between the upper and lower surface of an aerofoil?
Thickness
What is the distance between the line averaging the midpoint of the upper and lower surface and the chord line?
Camber
What is the line representing the midpoint between the upper and lower surface of an aerofoil?
Mean camber line
What is the furthest downstream point of an aerofoil?
Trailing edge
What is the distance between the leading edge and trailing edge of an aerofoil?
Chord
What happens when an aerofoil stalls?
Boundary layers separate from the upper surface, causing a massive increase in drag and decrease in lift
What is the zero-lift Angle of Attack
Angle at which the lift is zero
How does a trailing edge flap with positive deflection impact the lift curve?
Increases the lift coefficient at a given angle of attack by increasing “effective” camber
How is the zero lift angle of attack impacted by a trailing edge flap?
It decreases (more camber)
What can be added to an aerofoil to increase the maximum lift coefficient and stall angle?
Leading Edge Flaps
How is the drag affected by adding a high-lift device?
It increases
What is the finesse of an aerofoil?
Lift to drag ratio
