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Exam Details

Aerospace Engineering (AE) 2008

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Questions 85
Duration 180 mins
Package Aerospace Engineering (AE) - Previous Year Papers

Paper pattern & analysis

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Showing all 85 questions in this paper.

Subject distribution

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Topic distribution

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Subtopic distribution

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Difficulty distribution

Easy 85 100%

Question type distribution

Multiple Choices 85 100%

Instructions

Aerospace Engineering (AE) 2008 – Instructions
  • Total number of questions: 85
  • 20 questions carry one mark each
  • 65 questions carry two marks each
  • Negative marking: 1/4 of the marks allotted to the question
  • Use of calculator is allowed
  • This is a proctored examination
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Syllabus

Full Syllabus

Sample questions from this paper

Questions are selected across the paper subjects wherever the paper contains that variety.

1
2008 · Unclassified
Aerospace Engineering (AE) 2008
Q.1 – Q.20 carry one mark each.

The function defined by f(x) = sin x, x < 0 0, x = 0 3x2, x > 0

A
is neither continuous nor differentiable at x = 0
B
is continuous and differentiable at x = 0
C
is differentiable but not continuous at x = 0
D
is continuous but not differentiable at x = 0
2
2008 · Unclassified
Aerospace Engineering (AE) 2008

The product of the eigenvalues of the matrix

Question diagram

is
A
4
B
0
C
−6
D
−9
3
2008 · Unclassified
Aerospace Engineering (AE) 2008

Which of the following equations is a LINEAR ordinary differential equation?

A
d²y/dx² + dy/dx + 2y² = 0
B
d²y/dx² + dy/dx + 2y = 0
C
d²y/dx² + (dy/dx)² + 2y = 0
D
(dy/dx)² + dy/dx + 2y = 0
4
2008 · Unclassified
Aerospace Engineering (AE) 2008

To transfer a satellite from an elliptical orbit to a circular orbit having radius equal to the apogee distance of the elliptical orbit, the speed of the satellite should be

A
increased at the apogee
B
decreased at the apogee
C
increased at the perigee
D
decreased at the perigee
5
2008 · Unclassified
Aerospace Engineering (AE) 2008

The service ceiling of a transport aircraft is defined as the altitude

A
that is halfway between sea-level and absolute ceiling
B
at which it can cruise with one engine operational
C
at which its maximum rate of climb is zero
D
at which its maximum rate of climb is 0.508 m/s
6
2008 · Unclassified
Aerospace Engineering (AE) 2008

The drag of an aircraft in steady climbing flight at a given forward speed is

A
inversely proportional to climb angle
B
higher than drag in steady level flight at the same forward speed
C
lower than drag in steady level flight at the same forward speed
D
independent of climb angle