Flight Theory and Aerodynamics. Joseph R. Badick

airfoil

      Trim systems

      Vertical axis

      Yaw

      PROBLEMS

      1 Flight control systems are of two types:first and second.primary and secondary.trim systems and tabs.balanced and imbalanced.

      2 During a turn to the right, the aileron on the right wing is deflected:up.down.in the same direction as the aileron on the left wing.neither up or down as it remains stationary.

      3 During the transition from level flight to a climb attitude in a light aircraft, as the control stick is moved aft, the elevator or stabilator is positioned to produce a _______ by deflecting the elevator/stabilator _______.a tail‐up force/upward.a tail‐down force/upward.a tail‐down force/downward.a tail‐up force/downward.

      4 The rudder controls movement around the:longitudinal axis.lateral axis.vertical axis.

      5 Deploying trailing edge flaps increases lift and drag.TrueFalse

      6 Number 3 on the drawing showsthe chord line.the maximum camber.the thickness.the mean camber line.

      7 Number 4 on the drawing showsthe chord line.the thickness.the maximum camber.the mean camber line.

      8 Number 5 on the drawing showsthe maximum camber.the mean camber line.the upper‐surface curvature.the maximum thickness.

      9 Which of the following is not considered a primary variable in the geometry of an airfoil?airfoil composition.shape of the mean camber line.leading edge radius.location of the maximum thickness.

      10 The Magnus effect explains whya bowling ball curves.a pitched baseball curves.a golf ball slices.Both (b) and (c).

      11 Which of the following will develop positive lift?A symmetrical airfoil at zero AOA.A nonrotating cylinder in a wind tunnel.A cambered airfoil at zero AOA.

      12 Which of the following will not produce a pitching moment?A symmetrical airfoil at a positive AOA.A cambered airfoil that is developing zero lift.A cambered airfoil that is at a positive AOA.A symmetrical airfoil at zero AOA.Both (a) and (d).

      13 The aerodynamic center (AC) is located at50% C subsonically and 25% C supersonically.25% C at all speeds.50% C at all speeds.25% C subsonically and 50% C supersonically.

      14 For a cambered airfoil, the center of pressure (CP)moves to the rear of the wing at low AOA.moves backward as AOA increases.moves forward as AOA increases.Both (a) and (c).

      15 Which of these statements is false? For a cambered airfoil,the AC is where all changes in lift effectively take place.there is no pitching moment at the AC.the AC is located near 25% C subsonically.the pitching moment at the AC is constant with change of AOA (at constant airspeed).

      16 For a symmetrical airfoil,the center of pressure moves forward as AOA increases.the center of pressure stays at the same place as AOA increases.there is no pitching moment about the CP.Both (b) and (c).