Lift And CL coefficient

Question 1

What is the lift formula?

Answer 1

L= W =CL x rho/2 x V2 x S

For straight and level flight lift and weight must be equal.

Surface and density are usually contrast and thus speed and coefficient are the variables.

They are inversely proportional.

Question 2

Where does a positively cambered wing intersect the horizontal line on a CL v AOA graph?

Answer 2

Left of the origin (a postive camber needs negative AOA to generate no lift)

Question 3

Where does a positively cambered wing intersect the vertical line on a CL v AOA graph?

Answer 3

Above the origin (even at 0 AOA a positive wing still generates some lift)

Question 4

Where does a negatively cambered wing intersect the horizontal line on a CL v AOA graph?

Answer 4

Right of the origin (will stop producing lift at a lower postive AOA)

Question 5

Where does a negatively cambered wing intersect the vertical line on a CL v AOA graph?

Answer 5

Below the origin

Question 6

Where does a symmetrically cambered wing intersect the horizontal line on a CL v AOA graph?

Answer 6

at the origin point. (no AOA = no lift)

Question 7

Any aerodynamic force is the product of?

Answer 7

(q) Dynamic Pressure
(S) Surface Area
coefficient of the force