Open FoilSim. Use the program to answer the following questions.

1. Design an airfoil (wing) that can supply at least 5,000 lbs. of lift at an altitude of 10,000 ft. with a minimum airspeed of 210 mph.

   Airfoil Data:

   Airspeed	Altitude	Angle	Thickness	Camber	Area	Lift
   210 mph	10,000 ft.

    
2. Record the data from Problem 1 into Table 1. Alter or vary the value of the air density (change air density by altering ALTITUDE) while keeping the other variables the same. Record the changes in the lift in Table 1 for five different air densities in Rows 1 - 5.

   In the lift equation, lift is L, air density is r, and air speed is v.  

   	Lift	Air Density	Airspeed	Constant
   1
   2
   3
   4
   5
   6
   7
   8
   9
   10
   11
   12
   13
   14
   15

3. Vary the airspeed and record the changes in lift in Rows 6 - 10.
4. Vary the airfoil area and record the changes in lift in Rows 11 - 15.
5. Use the equation L = constant x r x v² to solve for the constant in Table 1.
6. Using graph paper, plot lift versus air density.
7. Did you expect this type of graph?
8. If the graph is linear, calculate the slope of the line.
9. Using graph paper, plot lift versus velocity.
10. Did you expect this type of graph?
11. If the graph is linear, calculate the slope of the line.
12. Using graph paper, plot lift versus constant.
13. What can you determine from this graph?