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Previous year question hub

Static stability - Flight Mechanics & Space Dynamics - Aerospace Engineering Previous Year Questions

Practice Static stability - Flight Mechanics & Space Dynamics - Aerospace Engineering previous year questions organised from real papers, with year-wise coverage and clear topic navigation.

2Papers
2Years
6Questions
1Topics

Static stability question pattern

Every graph below is calculated only from this selection.

Questions by year

Year-wise coverage for Static stability. Each bar uses a separate theme-derived color.

Difficulty distribution

How the classified questions are distributed by difficulty.

Easy 4 66.7%
Medium 2 33.3%

Question type distribution

MCQ, numerical, multiple-select and other formats found in these papers.

Multiple Choices 5 83.3%
Numerical Answer Type (NAT) 1 16.7%

Subject weightage

Top subjects by unique question coverage.

Aerospace Engineering
6 Qs

Most asked topics

Top topics across the included previous year papers.

Flight Mechanics & Space Dynamics
6 Qs

Subtopic coverage

Top subtopics inside this exact selection.

Static stability
6 Qs

Paper coverage

Question coverage for the most populated papers. Every active PYP paper remains listed below.

Aerospace Engineering (AE) 2026
2 Qs
Aerospace Engineering (AE) 2025
4 Qs

Included previous year papers

Newest papers appear first. Sort by year, question coverage or name.

PaperYear / sessionQuestions in this viewOpen
Aerospace Engineering (AE) 202620262View paper
Aerospace Engineering (AE) 202520254View paper

All Static stability previous year questions

Practice every matching question in batches of 20, with every available option.

1
2025 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Static stability
Aerospace Engineering (AE) 2025

A general aviation airplane is in steady and level flight. The airplane is prone to adverse yaw. Which one of the following options best describes the deflections of aileron and rudder to achieve a coordinated right turn?

A
Left aileron: down; Right aileron: up; Rudder: left
B
Left aileron: down; Right aileron: up; Rudder: right
C
Left aileron: up; Right aileron: down; Rudder: left
D
Left aileron: up; Right aileron: down; Rudder: right
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2
2025 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Static stability
Aerospace Engineering (AE) 2025

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

A
Wing with a positive dihedral angle
B
Fuselage with a high wing
C
Fuselage with a low wing
D
Swept back wing
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3
2025 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Static stability
Aerospace Engineering (AE) 2025

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

A
The center of gravity of the airplane should be aft of the neutral point.
B
The center of gravity of the airplane should be forward of the neutral point.
C
The stability coefficient \(\frac{\partial C_m}{\partial \alpha}\) (\(C_m\) is the airplane pitching moment coefficient and \(\alpha\) is the angle of attack) is positive.
D
The static margin is negative.
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4
2025 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Static stability
Aerospace Engineering (AE) 2025
A general aviation airplane is initially in steady and level flight. The stability coefficient \(\frac{\partial C_m}{\partial q}\) (\(C_m\) is the airplane pitching moment coefficient and \(q\) 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 unsteady effects are neglected. When compared to steady and level flight condition, which of the following statements is/are true during the perturbed motion?
A
The angle of attack of the horizontal tail increases.
B
The contribution of the horizontal tail to the airplane’s pitching moment about the center of gravity is more stabilizing.
C
The lift generated by the horizontal tail increases.
D
The contribution of the horizontal tail to the airplane’s pitching moment about the center of gravity is less stabilizing.
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5
2026 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Static stability
Aerospace Engineering (AE) 2026

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

A

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

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

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

D
Dynamic stability is related to the time history of aircraft motion after being disturbed from its equilibrium position
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6
2026 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Static stability
Aerospace Engineering (AE) 2026
The response x(t) of a freely vibrating single degree of freedom underdamped system is given below. In the equation, A and φ are constants. The damping ratio of the system is _______ (rounded off to 3 decimal places).
\( x(t) = A e^{-5t} \sin(10t + \phi) \)
Enter a numerical response
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