GATE AE topic:static-stability PYQs & Answers — Page 2

Questions 11–20 of 25. Imported answers require independent review unless marked reviewed.

A conventional fixed-wing aircraft, with a horizontal tail and vertical fin, in steady and level flight is subjected to small perturbations. Which of the following statement(s) is/are true?

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

Vertical fin has a stabilizing effect on the lateral stability of the aircraft.

Vertical fin has a destabilizing effect on the directional stability of the aircraft.

Presence of wing anhedral increases the lateral stability of the aircraft.

Horizontal tail has a stabilizing effect on the longitudinal static stability of the aircraft.

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Consider a jet transport airplane with the following specifications:

Lift curve slope for wing-body

/deg Lift curve slope for tail

/deg Tail area

Wing area

Distance between mean aerodynamic centers of tail and wing-body

m Mean aerodynamic chord

m Downwash

Axial location of the wing-body mean aerodynamic center

Axial location of the center of gravity

All axial locations are with respect to the leading edge of the root chord and along the body x-axis. Ignore propulsive effects.

The pitching-moment-coefficient curve slope (

) is ______ /deg (round off to three decimal places).

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For conventional airplanes, which one of the following is true regarding roll control derivative

and yaw control derivative

, where

is rudder deflection?

Your answerChoose one option.

and

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For three different airplanes A, B and C, the yawing moment coefficient (

) was measured in a wind-tunnel for three settings of sideslip angle

and tabulated as:

Sideslip angle	Airplane A	Airplane B	Airplane C
deg	-0.030	-0.025	0.040
deg	0	0	0
deg	0.030	0.025	-0.040

Which one of the following statements is true regarding directional static stability of the airplanes A, B and C?

Your answerChoose one option.

All three airplanes A, B and C are stable.

Only airplane C is stable, while both A and B are unstable.

Airplane C is unstable, A and B are stable with A being more stable than B.

Airplane C is unstable, A and B are both stable with A less stable than B.

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For a general aviation airplane with tail efficiency

, horizontal tail volume ratio

, downwash angle slope

, wing lift curve slope

rad⁻¹, horizontal tail lift curve slope

rad⁻¹, shift in neutral point location as a percentage of mean aerodynamic chord is ______ (round off to two decimal places).

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Which of the following graphs represents the response of a dynamically unstable airplane?

Your answerChoose one option.

Diagram for Aerospace Engineering question 9

Diagram for Aerospace Engineering question 9 (figure 2)

Diagram for Aerospace Engineering question 9 (figure 3)

Diagram for Aerospace Engineering question 9 (figure 4)

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Which of the following statements about adverse yaw of an airplane is/are correct? P. It is caused by flow separation resulting from large rudder deflection. Q. It is caused by dissimilar drag forces acting on the two halves of the wing resulting from aileron deflections of same magnitude. R. It can be eliminated by ensuring that the upward deflection of one aileron is greater than the downward deflection of the opposite aileron.

Your answerChoose one option.

P only

Q only

P and R

Q and R

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The design of an airplane is modified to increase the vertical tail area by 20% and decrease the moment arm from the aerodynamic centre of the vertical tail to the airplane centre of gravity by 20%. Assuming all other factors remain unchanged, the ratio of the modified to the original directional static stability (

due to tail fin) is ______ (round off to 2 decimal places).

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The pilot of a conventional airplane that is flying steady and level at some altitude, deflects the port side aileron up and the starboard aileron down. The aircraft will then

Your answerChoose one option.

pitch, nose up.

roll with the starboard wing up.

pitch, nose down.

roll with the port wing up.

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A statically-stable aircraft has a

(where the angle of attack,

, is measured in radians). The coefficient of moment of the aircraft about the center of gravity is given as

. The mean aerodynamic chord of the aircraft is 1 m. The location (positive towards the nose) of the neutral point of the aircraft from the center of gravity is _____ (in m, accurate to two decimal places).

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GATE AE topic:static-stability PYQs

Question 36

Question 55

Question 12

Question 31

Question 45

Question 9

Question 28

Question 44

Question 5

Question 41