Steady Level Flight-1 MCQ

Test your knowledge with important Steady Level Flight-1 MCQ and their applications. These MCQs are beneficial for competitive exams too. Explore 30 + more Steady Level Flight-1 MCQs at Bissoy

• Find the drag at which thrust required is minimum. Consider CD0 as 0.015 and reference area is 5m2. Consider steady level flight with q of 15Pa.
  ক

  2.25N

  খ

  22.5N

  গ

  225N

  ঘ

  2250N
• Which of the following is required condition of thrust required minimum?
  ক

  CL = (CD0/K)0.5

  খ

  CL = (CD0)*0.21

  গ

  CL = (CD0/K)*1.5

  ঘ

  CL = 0.5
• If lift coefficient at thrust required minimum is 0.85 and induced drag factor K is 0.0085 then, find the approximate value of drag coefficient at zero lift.
  ক

  0.0061

  খ

  0.061

  গ

  0.61

  ঘ

  6.1
• Find the velocity for minimum thrust required at steady level flight if wing loading is 75N/m2 and induced drag factor K is 0.0025. Consider CD0 as 0.02 and density as sea level.
  ক

  6.45m/s

  খ

  97m/s

  গ

  120m/s

  ঘ

  75m/s
• We can design our aircraft to cruise for 3 different lift to drag ratio. Lift to drag ratio are as follows: 10, 12 and 11.25. Now, if we want to reduce thrust required to fly then, at which value of lift to drag ratio our aircraft needs to be designed so that it can operate with minimum thrust required?
  ক

  12

  খ

  10

  গ

  11.25

  ঘ

  10.62
• Let’s consider our aircraft has to generate thrust of 150KN during cruise. If at the cruise thrust loading is 0.86 then, at which value of Lift our aircraft is flying?
  ক

  174.4KN

  খ

  450KN

  গ

  100N

  ঘ

  174N
• If an aircraft is in steady level flight and weighs 2500 kg then, find lift at the given flight condition.
  ক

  24.525KN

  খ

  24525kg

  গ

  2500 N

  ঘ

  35000kg
• An aircraft is designed with lift coefficient of 1.1 during steady level flight. If dynamic pressure is set to be 25.65 Pa then find weight of aircraft during this flight condition.
  ক

  28.215 N per unit area

  খ

  30 kg

  গ

  59 N

  ঘ

  125.25 N
• An aircraft has to be designed to operate at aerodynamic efficiency of 10 at cruise. Find the required thrust to weight ratio for maintaining this unaccelerated steady level flight.
  ক

  0.1

  খ

  0.6

  গ

  1.5

  ঘ

  10.45
• Which of the following is correct for steady level flight?
  ক

  T=D

  খ

  T>D

  গ

  D<T

  ঘ

  L>W
• If my aircraft is in steady level flight and has thrust of 100 unit then, what will be the approximate value of time Easter if change of aircraft weight. Consider SFC as C unit.
  ক

  -100C

  খ

  1000

  গ

  1.25

  ঘ

  5.43
• Find climb angle of climb gradient is 0.6. Assume non accelerated flight.
  ক

  31°

  খ

  1.2

  গ

  4.5rad

  ঘ

  9.94°