My Cart
Your Cart 0

    Your cart is empty.

  • Total (Amount) ₹0.00
Exam Details

Aerospace Engineering (AE) 2009

Review the key details, then start the test when you are ready. You can also open the full package to see related papers.

Questions 60
Duration 180 mins
Package Aerospace Engineering (AE) - Previous Year Papers

Paper pattern & analysis

Filter this paper by subject, topic or subtopic. Every graph updates from the selected questions.

Explore previous papers
Showing all 60 questions in this paper.

Subject distribution

No subject classification is available.

Topic distribution

No topic classification is available.

Subtopic distribution

No subtopic classification is available.

Difficulty distribution

Easy 60 100%

Question type distribution

Multiple Choices 60 100%

Instructions

Aerospace Engineering (AE) 2009 – Instructions
  • Total number of questions: 60
  • 20 questions carry one mark each
  • 40 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
  • All other browser applications will be automatically closed
  • 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
2009 · Unclassified
Aerospace Engineering (AE) 2009
Q.1 – Q.20 carry one mark each.

For a flow through a Prandtl-Meyer expansion wave

A
Mach number stays constant.
B
Entropy stays constant.
C
Temperature stays constant.
D
Density stays constant.
2
2009 · Unclassified
Aerospace Engineering (AE) 2009

For two-dimensional irrotational and incompressible flows

A
Both potential and stream functions satisfy the Laplace equation.
B
Potential function must satisfy the Laplace equation but the stream function need not.
C
Stream function must satisfy the Laplace equation but the potential function need not.
D
Neither the stream function nor the potential function need to satisfy the Laplace equation.
3
2009 · Unclassified
Aerospace Engineering (AE) 2009

A trailing edge plain flap deflected downward increases the lift coefficient of an airfoil by

A
Increasing the effective camber of the airfoil.
B
Delaying the separation of the flow from the airfoil surface.
C
Increasing the local airspeed near the trailing edge.
D
Controlling the growth of the boundary layer thickness along the airfoil surface.
4
2009 · Unclassified
Aerospace Engineering (AE) 2009

Thin airfoil theory predicts that the lift slope is dCl/da = 2π for

A
Symmetric airfoils only.
B
Cambered airfoils only.
C
Any airfoil shape.
D
Joukowski airfoils only.
5
2009 · Unclassified
Aerospace Engineering (AE) 2009

The ordinary differential equation d2y/dx2 + ky = 0 where k is real and positive

A
is non-linear
B
has a characteristic equation with one real and one complex root
C
has a characteristic equation with two real roots
D
has a complementary function that is simple harmonic
6
2009 · Unclassified
Aerospace Engineering (AE) 2009

A non-trivial solution to the (n×n) system of equations [A]x = 0, where 0 is the null vector

A
can never be found
B
may be found only if [A] is not singular
C
may be found only if [A] is an orthogonal matrix
D
may be found only if [A] has at least one eigenvalue equal to zero