NAME_________________________________ CLASS____________________ DATE____________
I. For each of the tables below:
a) Set the following conditions:
Airspeed = 100 mph
Altitude = 0 feet
Angle = 0 degrees
Thickness = 12.5%
Camber = 0
Area = 1.0 sq ft
b) Assume and enter the following for each aircraft:
Altitude = 0 feet
Angle = 0 degrees
Thickness = 12.5%
Camber = 5%
c) Enter the areas you determined for each aircraft (both
wings) from the Wing Area
Investigations Activity.
{Hint: Lift and Area are directly proportional. If the area
is over 1000 sq. ft., then divide it by 10 and enter that number.
When you get the lift, multiply it by 10 to get the real
value!}
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wings: |
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wings: |
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II. Review the values entered in FoilSim.