NAME_________________________________ CLASS____________________ DATE____________

__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.

Wing Area (ft^{2})Lift (lbs)

__Step 2.__

Graph your recorded data for wing area and lift below.

__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. Pick 5 different
values for the altitude. Record the resulting values for density and
the resulting lift.

Density (slug/ft^{3})Lift (lbs)

__Step 5.__

Graph your recorded data for density and lift below.

__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.
Pick 5 different values for the velocity. Record the values you used
for velocity and the resulting lift.

Velocity (ft/sec)Lift (lbs)

__Step 8.__

Graph your recorded data for velocity (airspeed) and lift below.

__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 190ft./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.)