GATE AE Static Stability PYQs & Answers

Questions 1–10 of 25. Imported answers require independent review unless marked reviewed.

Which of the following statements is/are TRUE about the stability of an aircraft?

Your answerSelect all correct options. You can choose more than one.

Static stability of an aircraft is sufficient to guarantee its dynamic stability

Static stability of an aircraft is related only to its initial tendency to return towards the equilibrium position from which it is disturbed

An aircraft may be dynamically unstable even if it is statically stable

Dynamic stability is related to the time history of aircraft motion after being disturbed from its equilibrium position

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For a general aviation airplane, which one of the following has a destabilizing effect on its static roll stability?

Your answerChoose one option.

Wing with a positive dihedral angle

Fuselage with a high wing

Fuselage with a low wing

Swept back wing

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To achieve longitudinal static stability of a general aviation airplane, which one of the following conditions should be satisfied?

Your answerChoose one option.

The center of gravity of the airplane should be aft of the neutral point.

The center of gravity of the airplane should be forward of the neutral point.

The stability coefficient

(

is the airplane pitching moment coefficient and

is the angle of attack) is positive.

The static margin is negative.

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A general aviation airplane is initially in steady and level flight. The stability coefficient

(

is the airplane pitching moment coefficient and

is the pitch rate) is negative. The airplane is perturbed with a small nose-up constant pitch rate. Assume that the horizontal tail does not stall during the perturbation, and instead effects are neglected. When compared to steady and level flight condition, which of the following statements is/are true during the perturbed motion?

Your answerSelect all correct options. You can choose more than one.

The angle of attack of the horizontal tail increases.

The contribution of the horizontal tail to the airplane’s pitching moment about the center of gravity is more stabilizing.

The lift generated by the horizontal tail increases.

The contribution of the horizontal tail to the airplane’s pitching moment about the center of gravity is less stabilizing.

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In a conventional configuration airplane, the rudder can be used:

Your answerSelect all correct options. You can choose more than one.

to overcome adverse yaw during a turning maneuver

to overcome yawing moment due to failure of one engine in a multi engine airplane

for landing the airplane in crosswind conditions

for enhancing longitudinal stability

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For an airplane having directional / weathercock static stability, which of the following options is/are correct?

Your answerSelect all correct options. You can choose more than one.

The airplane when disturbed in yaw, from an equilibrium state, will experience a restoring moment

The variation of yawing moment coefficient (

) with sideslip angle (

) for the airplane will look like

Diagram for Aerospace Engineering question 48

The airplane will always tend to point into the relative wind

The airplane when disturbed in yaw will return to equilibrium state in a finite amount of time after removing the disturbance

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For a longitudinally statically stable aircraft, which one of the following represents the relationship between the coefficient of pitching moment about the center of gravity

and absolute angle of attack

? (Note: nose-up moment is positive.)

Your answerChoose one option.

Diagram for Aerospace Engineering question 19

Diagram for Aerospace Engineering question 19 (figure 2)

Diagram for Aerospace Engineering question 19 (figure 3)

Diagram for Aerospace Engineering question 19 (figure 4)

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Regarding the horizontal tail of a conventional airplane, which one of the following statements is true?

Your answerChoose one option.

It contributes to

It makes

and

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variation for a certain aircraft is shown in the figure. Which one of the following statements is true for this aircraft?

Diagram for Aerospace Engineering question 13

Your answerChoose one option.

The aircraft can trim at a positive

and it is stable.

The aircraft can trim at a positive

, but it is unstable.

The aircraft can trim at a negative

and it is stable.

The aircraft can trim at a negative

, but it is unstable.

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An aircraft with twin jet engines has the following specifications:

Thrust produced (per engine) = 800 N

Spanwise distance between the two engines = 10 m

Wing area = 50 m², Wing span = 10 m

Rudder effectiveness,

/deg

Density of air at sea level = 1.225 kg/m³

The rudder deflection, in degrees, required to maintain zero sideslip at 100 m/s in steady and level flight at sea level with a non-functional right engine is ______ (round off to two decimal places).

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GATE AE Static Stability PYQs

How to practice Static Stability

Question 23

Question 23

Question 25

Question 38

Question 27

Question 48

Question 19

Question 19

Question 13

Question 24