Once the data from the 1903 Wright Flyer replica have been posted, have the students use the following data columns to graph the CM vrs. Alpha:

	Run #61, #62, #63
	Alpha (=Angle of Attack)
	CM
	Delta sub e (=Angle of Canard)

Use the guide sheet below to assist students in graphing the data.

After plotting the data for the 0ƒ, +10ƒ, -10ƒ angle of attack, have the students connect the points to form the 3 slopes. Have them compare the slope to that of a stable airplane by using the answer key from Activity #1.

The students should notice that the slopes are remarkably different. That is due to the statically unstable nature of the original design in that it does not return to its original flight path without the pilot having to adjust the controls. For the most part, aeronautical researchers and historians believe that to maintain control of the aircraft, whichever brother was piloting the aircraft would continually be making adjustments to the control surfaces throughout the flight in order to maintain balance.

First, plot the points for only "Run #62" from the "Alpha" and the "CM" columns. During this wind tunnel test, the elevator was set at 0 degrees angle of attack. The angle of attack is indicated by the data in last column which is the delta sub "e" (canard deflection angle). Connect these points with a black line.

Second, plot the points for "Run #61" from the "Alpha" and the "CM" columns. During this wind tunnel test, the elevator was set at a positive pitch of +5 degrees. The angle of attack is indicated by the data in the column which is the delta sub "e" (canard deflection angle). Connect these points with a blue line.

Third, plot the points for "Run #63" from the "Alpha" and the "CM" columns. During this wind tunnel test, the elevator was set at a negative pitch of -5 degrees. The angle of attack is indicated by the data in last column which is the delta sub "e" (canard deflection angle). Connect these points with a red line.

Remember to begin with a graph as shown below.