1) Show, by a drawling below, how a v velocity on the following airplane can become a
u
. What angular rate would need to be present ? Show 2 frames of the motion.
2) Show, by a drawling below, how a w velocity on the following airplane can become a
What angular rate would need to be present ?
3) Sketch on the following airplane an explanation for dihedral effect due to wing placement on the fuselage .
v
w
4) Sketch on the following airplane an explanation for dihedral effect due to dihedral angle of the wings on the fuselage .
5) Draw a diagram that explains the change in angle of attack on the canard on the canard due to a pitch rate, q. Show how CMq will change. Make sure to include a drawing of the CG, freestream, pitch rate direction, the induced flow on the canard, the induced angles on the canard and the resulting forces and moments.
6) Show the derivation of glide ratio on the following diagram. Make sure to include the relative wind and the proper vectors for lift and drag. Indicate all angles that are perpendicular and those that are the same value.
7) A tailwheel airplane is making a right 180-degree turn on the ground. Show an approximate time history of the rudder pedal deflection required to do this. Absolute values are unimportant. The correct sign and relative values are critical.
W
Right
Left
Start End
8) An airplane is taking off in a crosswind. Just prior to lift off, the fuselage is aligned with the centerline and there is a balance of forces into and away from the wind as seen in the top view below:
Sketch the rear view of the aircraft with the appropriate into and away from the wind forces. Label each force. And, if associated with a stability derivative, indicate which derivative. Assume that the normal force on the tire is low and the tires are unable to produce into the wind and way from the wind forces.
9) On this rear view of an aircraft, draw the proper deflection of the ailerons to produce a positive rolling moment. Draw a depiction of the lift distribution on the wing showing the positive rolling moment.
10) Draw a diagram that explains
CNr
on a Piper Cherokee below. Show the change in angle of attack
on the appropriate surface due to a yaw rate. Make sure to include a drawing of the CG, your direction for r, the local angle of attack due to r, direction of the additional lift and the direction of the resulting moment.
11) Draw a diagram that explains
CN on a Piper Cherokee below. Show the change in angle of attack
on the appropriate surface due to a side slip. Make sure to include a drawing of the CG, your direction for side slip, the direction of the additional lift and the direction of the resulting moment.
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