AOA

Question 1

AOA = 0 when
AOA = positive when

Answer 1

AOA is between air flow and chord line.

Leading edge pointer upwards, causing the air flow to be forced down wards more

Question 2

Types of camber

Answer 2

Positive chamber, leading edge pointed downwards.
Negative chamber, leading edge upside down and pointed upwards.
Symmetrical.
Bi convex thin. Pointy leading edge

Question 3

Thickness:Chord ratio ?

Answer 3

Max thickness (up and below the wing, in air flow) to where the chord line is.

Question 4

0⚫️AOA creates

Answer 4

DRAG, NO LIFT

Question 5

The higher AOA the…

Answer 5

Steeper the pressure gradient

Question 6

At pressure gradient 16⚫️

Answer 6

Air flow separates from wing. Means stall

Question 7

Aerodynamic force equation

Answer 7

1/2 p X v^2 X S X CADF
1/2 density x velocity squared x surface area x coefficient of aerodynamic force.
Done to work out whether you can sustain lift.
Velocity must be in m/s

Question 8

The coefficient of aerodynamic force is the

Answer 8

Aerodynamic force per unit of dynamic pressure and area.

Question 9

The coefficient of lift depends on:

Answer 9

CAT

camber, AOA, thickness

Question 10

If speed increases, then CL must

Answer 10

Come down

Question 11

CL max=

Answer 11

Critical alpha

Question 12

As CL increases

Answer 12

Thickness increases

Greater thickness of wing, the better the air can flow over it