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 (indicate variable and sign)? 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 (indicate variable and sign)?
3) Sketch on the following airplane an explanation for dihedral effect due to wing placement on the
fuselage (indicate the wind direction, the net rolling moment and appropriate streamlines).
v
w
4) Sketch on the following airplane an explanation for dihedral effect due to dihedral angle of the wings
(and only dihedral angle of the wings) on the fuselage (indicate the wind direction, the net rolling
moment, a cross section of the flow on airfoil of both the left and right wings and appropriate
streamlines).
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 sideslip. Make sure to include a drawing of the CG, your direction
for sideslip, the direction of the additional lift and the direction of the resulting moment.
