Lift
Equation Activity
If so instructed by your teacher, print out a worksheet
page for these problems.
Open
FoilSim .
Use the Flight Test, Shape, and Size input panels to set the following
conditions:
Airspeed

100

Altitude

0

Angle

0.0

Thickness

12.5

Camber

5.0

Area

1

Step 1.
Using FoilSim, change
the values for Area only. Pick 5 different values for the wing
area. Record the values you used for area and the resulting lift.
Step 2.
Graph your recorded
data for wing area and lift.
Step 3.
State the relationship
between area and lift.
Step 4.
Using FoilSim, change
the values for Altitude only. Reset the airfoil conditions to the original
values given above. Pick 5 different values for the altitude. Record the resulting
values for density and the resulting lift.
Step 5.
Graph your recorded
data for density and lift.
Step 6.
State the relationship
between density and lift.
Step 7.
Using FoilSim,
change the values for Velocity (airspeed) only. Reset the airfoil
conditions to the original values given above. Pick 5 different values for the velocity.
Record the values you used for velocity and the resulting lift.
Step 8.
Graph your recorded
data for velocity (airspeed) and lift.
Step 9.
State the relationship
between the velocity and the lift.
Step 10.
Using the lift equation,
calculate the lift generated by an aircraft flying at 10,000 ft at a speed
of 120 ft./sec. The wing area is 500 ft.^{2 }and the lift coefficient
is 1.67. (You will need to use FoilSim or your graph to find the density
at the given altitude.)
Step 11.
Calculate the lift
coefficient for an aircraft with a 240 ft.^{2 }wing area and a
speed of 190 ft./sec. that can generate 9530 lbs. of lift in air with
a density of 0.00165 slug/ft.^{3}
Step 12.
Find the velocity
of an aircraft that generates 30,590 lbs. of lift when the wing area is
800 ft.^{2}. The lift coefficient for the aircraft is 1.4, and
the air density is 0.00089 slug/ft.^{3}
Step 13.
Using the graph you
constructed in Step 2, find the lift produced by a wing area of 1200 ft.^{2}
Step 14.
Using your graph from
Step 5 and FoilSim, find the altitude for an aircraft that generates a
lift of 15.39 lbs. (Remember: Set the airfoil conditions to the original
settings given at the beginning of this worksheet.)
