250+ TOP MCQs on Climb and Descent Performance with Thrust-Producing Engines and Answers

Aircraft Performance Multiple Choice Questions on “Climb and Descent Performance with Thrust-Producing Engines”.

1. Which of the following is the correct thrust balancing equation for thrust producing engines?
a) F_N+D=Wsinγ₂+mV̇
b) F_N-D=Wsinγ₂+mV̇
c) F_N-D=Wsinγ₂-mV̇
d) F_N+D=Wsinγ₂-mV̇
Answer: b
Clarification: The correct thrust balancing equation for thrust producing engines is given by the equation F_N-D=Wsinγ₂+mV̇ where F_N is the normal force acting on the aircraft, γ is the angle at which the force is acting on the aircraft, D is drag produced, W is weight of the aircraft, m is mass and V̇ is velocity.

2. Which of the following is the correct lift balancing equation for thrust producing engines?
a) L=Wcosγ₂
b) L=Wsinγ₂
c) L=(frac{cosgamma _2}{W})
d) L=(frac{singamma_2}{W})
Answer: a
Clarification: The correct lift balancing equation for thrust producing engines is given by the equation L=Wcosγ₂ where L is lift, W is weight and γ is the angle at which the force is acting on the aircraft.

3. What should be the value of thrust- to-weight ratio for a normal take-off so that the acceleration associated with the rate of climb is neglected?
a) 0.1
b) 0.2
c) 0.3
d) 0.4
Answer: c
Clarification: 0.3 must be the value of thrust- to-weight ratio for a normal take-off so that the acceleration associated with the rate of climb is neglected. This way the climb can be assumed with constant airspeed and mach number.

4. The best gradient of climb is attained at the time of maximum drag speed of the aircraft.
a) True
b) False
Answer: b
Clarification: The best gradient of climb is attained at the time of minimum drag speed of the aircraft. The best gradient of climb is attained generally at the airspeed ‘u’ of 1. The gradient of climb is given by E_maxsinγ₂=τ-(frac{1}{2})[u²+u^-2].

5. The best rate of climb occurs when the excess thrust power is minimum than drag power.
a) True
b) False
Answer: b
Clarification: The best rate of climb occurs when the excess thrust power (F_NV) is maximum than the drag power (DV). As the ideal power increases linearly with true airspeed the best gradient of climb is predicted to be at an airspeed greater than minimum drag speed.

6. The best gradient of climb is predicted to be at an airspeed greater than minimum drag speed.
a) True
b) False
Answer: a
Clarification: The best rate of climb occurs when the excess thrust power (F_NV) is maximum than the drag power (DV). As the ideal power increases linearly with true airspeed the best gradient of climb is predicted to be at an airspeed greater than minimum drag speed.

7. What is the relation between thrust power and true airspeed?
a) Thrust power increases with increase in true airspeed
b) Thrust power decreases with increase in true airspeed
c) Thrust power increases with decrease in true airspeed
d) Thrust power is independent of true airspeed
Answer: a
Clarification: Thrust power increases with increase in true airspeed.The best rate of climb occurs when the excess thrust power (F_NV) is maximum than the drag power (DV). As the ideal power increases linearly with true airspeed the best gradient of climb is predicted to be at an airspeed greater than minimum drag speed.

8. In which of the following the maximum rate of climb occurs?
a) It occurs when difference in thrust power and drag power is minimum
b) It occurs when difference in thrust power and drag power is maximum
c) It occurs when difference in thrust power is minimum
d) It occurs when difference in drag power is minimum
Answer: b
Clarification: The maximum rate of climb occurs when the difference in thrust power and drag power is maximum. The rate of climb is a function of excess thrust power.The best rate of climb occurs when the excess thrust power (F_NV) is maximum than the drag power (DV).

9. Which of the following is the correct climb gradient equation?
a) τ-(frac{1}{2})[u²+u^-2]=E_maxsinγ₂
b) τ+(frac{1}{2})[u²+u^-2]=E_maxsinγ₂
c) τ+(frac{1}{2})[u²+u^-2]=E_max
d) τ-(frac{1}{2})[u²+u^-2]=E_max
Answer: a
Clarification: The correct climb gradient equation is given by the equation τ-(frac{1}{2})[u²+u^-2]=E_maxsinγ₂ where τ is dimensionless thrust, u is airspeed, E_max is endurance and γ is the angle at which the force is acting on the aircraft.

10. At what airspeed does maximum gradient of climb occurs?
a) 1
b) 2
c) 3
d) 4
Answer: a
Clarification: The maximum gradient of climb occurs at airspeed (u) =1. There occurs negative values for sinγ₂ of τ and u when the flight is descending. The climb gradient equation is given by the equation τ-(frac{1}{2})[u²+u^-2]=E_maxsinγ₂.

11. Which of the following is the correct rate of climb equation?
a) τu-(frac{1}{2})[u³+u^-1]=E_maxv
b) τ-(frac{1}{2})[u²+u^-2]=E_maxsinγ₂
c) τ+(frac{1}{2})[u²+u^-2]=E_maxsinγ₂
d) τu-(frac{1}{2})[u³+u^-1]=E_maxv
Answer: d
Clarification: The correct rate of climb equation is given by τu-(frac{1}{2})[u³+u^-1]=E_maxv where τ is dimensionless thrust, u is airspeed, E_max is endurance and γ is the angle at which the force is acting on the aircraft.

12. What is the correct formula for dimensionless rate of climb?
a) ν=(frac{dH/dt}{V_{md}})
b) v=(frac{V_{md}}{dH/dt})
c) v=(frac{-V_{md}}{dH/dt})
d) v=(frac{-dH/dt}{V_{md}})
Answer: a
Clarification: The correct formula for dimensionless rate of climb is given by the formula v=(frac{dH/dt}{V_{md}}) where v the dimensionless rate of climb is and dH/dt is vertical velocity and V_md is velocity. The vertical velocity dH/dt is given in feet/min.

13. The minimum sink rate is attained by flying at a relative airspeed of u/(sqrt[4]{3}).
a) True
b) False
Answer: a
Clarification: The minimum sink rate is attained by flying at a relative airspeed of u/(sqrt[4]{3}). At this airspeed the minimum power speed of aircraft is attained. Flying at this speed will maximize the time of gliding flight.

14. What is the benefit of flying at minimum power speed?
a) Increases gliding flight time
b) Decreases gliding flight time
c) Does not change the gliding flight time
d) Decreases the aircraft performance
Answer: a
Clarification: The benefit of flying at minimum power speed is increase in gliding flight time. The minimum sink rate is attained by flying at a relative airspeed of u/(sqrt[4]{3}). At this airspeed the minimum power speed of aircraft is attained. Flying at this speed will maximize the time of gliding flight.

15. What is the value that maintains minimum power speed of the aircraft?
a) u/(sqrt[4]{3})
b) u/(sqrt[3]{3})
c) u²/(sqrt[4]{3})
d) u²/(sqrt[3]{3})
Answer: a
Clarification: The minimum sink rate is attained by flying at a relative airspeed of u/(sqrt[4]{3}). At this airspeed the minimum power speed of aircraft is attained. Flying at this speed will maximize the time of gliding flight.