Lift

Question 1

Coefficient of lift equation

Answer 1

L = IAS2 x S x cl

L = q x s x cl

Question 2

Increasing Alpha

Answer 2

CL increases up to critical angle of attack

Question 3

Units for CL

Answer 3

No unit as not a force/quantity

Question 4

Equation for CL

Answer 4

Cl = F/q x s

Question 5

Thickness of wing

Answer 5

CL Max increases
Increases Critical AOA
Able to fly slower
More drag

Question 6

Camber

Answer 6

Greater CL Max
Flaps used to change camber
Lower stalling AOA
Stagnation moves down
Increases pressure difference on upper lower surfaces

Defined as - max distance between the mean camber line and the chord line

Question 7

High vs low speed aerofoil

Answer 7

High - Lower Cl max and AOA
Low - Higher CL max and AOA

Question 8

Cl Max Is?

Answer 8

Greatest value coefficient of lift that can be achieved (same as critical angle)

Question 9

What effects CL max

Answer 9

CambeR
AOA (Alpha)
Thickness

(CAT)

Question 10

AOA (Alpha)

Answer 10

Increase CL

Question 11

Effect of decreased wing thickness

Answer 11

CLMAX decreases and stalling angle decreases

Question 12

Factors that change CLMAX

Answer 12

Camber
AOA
Thickness

Question 13

Does weight change the critical angle of attack

Answer 13

No

Question 14

Lift is generated when

Answer 14

Flow direction of certain mass of air is changed

Air moves over curved upper surface and travel faster therefore less pressure than underwing

Difference in pressure creates lift

Question 15

Lift

Answer 15

Acts perpendicular to the relative airflow (not always vertical component)

Question 16

Angle of attack of the aeroplane (NOT THE WING)

Answer 16

Angle between speed vector and longitudinal axis