Longitudinal Static Stability and Control-2 MCQ

Test your knowledge with important Longitudinal Static Stability and Control-2 MCQ and their applications. These MCQs are beneficial for competitive exams too. Explore 30 + more Longitudinal Static Stability and Control-2 MCQs at Bissoy

• Which of the following is correct to trim an aircraft at positive AOA?
  ক

  Cm0 > 0

  খ

  Cm0 < 0

  গ

  Cm0 will not affect positive trim AOA

  ঘ

  Every value of cm0 will trim at positive AOA
• Determine the corrections or otherwise of the following Assertion and Reason : Assertion : For longitudinal static stability of an aircraft, slope of moment curve should be negative. Reason: Positive slope will result in more static stability than negative slope. Hence, slope should be positive always. and are true and is the correct reason for b) Both and are true but is not the correct reason for c) is true but is false d) is false but is true
  ক

  and Reason : Assertion : For longitudinal static stability of an aircraft, slope of moment curve should be negative. Reason: Positive slope will result in more static stability than negative slope. Hence, slope should be positive always. ] Both and are true and is the correct reason for

  খ

  A

  গ

  A

  ঘ

  A
• If CM0 is -0.052 and lift coefficient at zero angle CL0 is 0.92 then, find CMac. Consider rectangular wing.
  ক

  -0.282

  খ

  0.98

  গ

  2.5

  ঘ

  7.89
• A rectangular wing has chord of 2m. Fond neutral point for this wing.
  ক

  50 cm

  খ

  290 cm

  গ

  189 cm

  ঘ

  267 m
• Find the appropriate value of pitching moment coefficient derivative if lift curve slope is 0.032 per degree and Xcg is 0.3. Consider neutral point is located at 60 % of chord from leading edge.
  ক

  -0.0096 per degree

  খ

  -7 per degree

  গ

  2.56 per degree

  ঘ

  0.1
• If SM = 0.12 and cg is located at 20% chord from l.e. then, find appropriate neutral point location.
  ক

  0.32

  খ

  0.87

  গ

  2.3

  ঘ

  1.54
• Determine required static margin if lift curve slope is 6.5 per rad and pitching moment coefficient slope as -0.58 per rad.
  ক

  8.9%

  খ

  78%

  গ

  0.89

  ঘ

  8.403
• Determine trim angle if, trim lift coefficient is 0.75 and lift curve slope is 4.5per rad. Consider elevator deflection as 1.056 per rad and trim elevator angle of 0.020 rad.
  ক

  0.1619 rad

  খ

  0.1619°

  গ

  2.98 rad

  ঘ

  34.23 rad
• Thrust will affect the stability of the aircraft.
  ক

  True

  খ

  False
• Canard will provide longitudinal static stability.
  ক

  False

  খ

  True
• If an aircraft has lift curve slope of 4.76 per rad and moment coefficient curve slope of -0.116 per rad then, find the location of neutral point. Consider Xcg=0.3.
  ক

  0.324

  খ

  0.9825

  গ

  23.45

  ঘ

  45.7
• An aircraft wing is experiencing AOA of 5°. If downwash due to wing is 2.6° then, how much angle is being seen by tail of the aircraft?
  ক

  2.4°

  খ

  4.5°

  গ

  6.7°

  ঘ

  1.23°