- #1

- 2

- 0

## Main Question or Discussion Point

This is a simple question hopefully.

The equation for determining lift produced by an aircraft is the following if I am correct:

L = (1/2) d v2 s CL

If I was designing an aircraft that would maintain flight at standard air pressure at 1000 feet .002308 ISA at 130 MPH with a wing area of 60 Sq Ft. and a Coefficient of lift of 1, then I would plug the numbers in accordingly..

(.5)*(.002308)*(130^2)*(60)*(1) = 1170

Would this mean that the maximum lift capacity for this type of plane be 1170 lbs, or am I way off base here?

The equation for determining lift produced by an aircraft is the following if I am correct:

L = (1/2) d v2 s CL

If I was designing an aircraft that would maintain flight at standard air pressure at 1000 feet .002308 ISA at 130 MPH with a wing area of 60 Sq Ft. and a Coefficient of lift of 1, then I would plug the numbers in accordingly..

(.5)*(.002308)*(130^2)*(60)*(1) = 1170

Would this mean that the maximum lift capacity for this type of plane be 1170 lbs, or am I way off base here?