Answer Posted / john p. lesslar
If this refers to an actual airplane, use the force lift
equation: FL=CL(pv^2/2)A, where;
CL = the lift coefficient determined by the shape of the air
foil and angle of attack (can be determined by just
referring to an air foil performance curve)
p = density of air in regards to temperature (again, just
check the necessary table)
v = velocity at which the plane leaves the ground (do not
forget to convert to [ft/s] or [m/s])
A = area of the wing (chord X span)
Plug in the values and obtain FL. If you used [ft] for your
units, your answer will be in [lbf]. If you used [m], your
answer will yield [N].
To determine the mass [kg], just divide your answer in [m]
by 9.81[m/s^2]
| Is This Answer Correct ? | 6 Yes | 2 No |
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