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Exam Details

Aerospace Engineering (AE) 2012

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Questions 65
Duration 180 mins
Package Aerospace Engineering (AE) - Previous Year Papers

Paper pattern & analysis

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Showing all 65 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 60 92.3%
Hard 5 7.7%

Question type distribution

Multiple Choices 60 92.3%
Fill in the blanks 5 7.7%

Instructions

Aerospace Engineering (AE) 2012 – Instructions
  • Total number of questions: 65
  • 30 questions carry one mark each
  • 35 questions carry two marks each
  • Negative marking: 1/3 of the marks allotted to the question
  • Use of calculator is allowed
  • This is a proctored examination
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  • After three warnings, the examination window will close automatically

Syllabus

Full Syllabus

Sample questions from this paper

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

1
2012 · Unclassified
Aerospace Engineering (AE) 2012
Q.1 – Q.25 carry one mark each.

The constraint A2 = A on any square matrix A is satisfied for

A
the identity matrix only.
B
the null matrix only.
C
both the identity matrix and the null matrix.
D
no square matrix A.
2
2012 · Unclassified
Aerospace Engineering (AE) 2012

The general solution of the differential equation d2y/dt2 + dy/dt - 2y = 0 is

A
Aeᵗ + Be²ᵗ
B
Ae²ᵗ + Beᵗ
C
Aeᵗ + Beᵗ
D
Ae²ᵗ + Be²ᵗ
3
2012 · Unclassified
Aerospace Engineering (AE) 2012

An aircraft in trimmed condition has zero pitching moment at

A
its aerodynamic centre.
B
its centre of gravity.
C
25% of its mean aerodynamic chord.
D
50% of its wing root chord.
4
2012 · Unclassified
Aerospace Engineering (AE) 2012

In an aircraft, constant roll rate can be produced using ailerons by applying

A
a step input.
B
a ramp input.
C
a sinusoidal input.
D
an impulse input.
5
2012 · Unclassified
Aerospace Engineering (AE) 2012

For a symmetric airfoil, the lift coefficient for zero degree angle of attack is

A
-1.0
B
0.0
C
0.5
D
1.0
6
2012 · Unclassified
Aerospace Engineering (AE) 2012

The critical Mach number of an airfoil is attained when

A
the freestream Mach number is sonic.
B
the freestream Mach number is supersonic.
C
the Mach number somewhere on the airfoil is unity.
D
the Mach number everywhere on the airfoil is supersonic.