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TS PGECET 2026
List of top Questions asked in TS PGECET- 2026
A vertical rocket has mass \(10,000\ \text{kg}\), thrust \(150,000\ \text{N}\) and drag \(20,000\ \text{N}\). The instantaneous acceleration (in \(\text{m/s}^2\)) is
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
Gravity loss during rocket flight occurs because
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
An eigen vector of the matrix \[ A= \begin{bmatrix} 3 & 2 1 & 2 \end{bmatrix} \] is
TS PGECET - 2026
TS PGECET
Mathematics
Linear Algebra
The matrix \[ A= \begin{bmatrix} 1 & 1+i & 2i 1-i & 3 & 4 -2i & 4 & 5 \end{bmatrix} \] has
TS PGECET - 2026
TS PGECET
Mathematics
Matrix
Fourier series of \(x^2,\;0<x<2\) is \[ f(x)=\frac{a_0}{2} +\sum_{n=1}^{\infty}a_n\cos(n\pi x) +\sum_{n=1}^{\infty}b_n\sin(n\pi x), \] then \(b_2=\)
TS PGECET - 2026
TS PGECET
Mathematics
Fourier series
A convergent series from the given series is
TS PGECET - 2026
TS PGECET
Mathematics
Convergence tests
Which of the following increases the thrust of a rocket engine?
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
A rocket produces maximum thrust in vacuum because
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
In multi-stage rockets, the stage mass fraction is defined as
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
Liquid chemical rockets are often classified by the type of propellants used. Which of the following is correct?
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
A rocket stage that ignites after the previous stage is jettisoned is called
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
Drag loss in a rocket flight is
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
Compressor surge occurs when
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Centrifugal Compressors
Specific impulse of a rocket engine is defined as
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
In a solid propellant rocket, the thrust level is primarily controlled by
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
For maximum thrust in a rocket nozzle, the exit pressure should be
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
One major advantage of liquid propellant rockets over solid propellant rockets is
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Rocket Propulsion
In an impulse turbine stage (degree of reaction \(=0\))
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Axial Turbines
For an axial turbine stage, the work done per unit mass flow is directly proportional to
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Axial Turbines
The work done per unit mass in a centrifugal compressor mainly depends on
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Centrifugal Compressors
The primary function of the inducer in a centrifugal compressor is to
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Centrifugal Compressors
A centrifugal compressor has an impeller tip speed of \(200\ \text{m/s}\). The whirl component of absolute velocity at the impeller exit is \(150\ \text{m/s}\). The whirl component of velocity at the inlet is zero. The specific heat at constant pressure is \(1\ \text{kJ/kg K}\). Using Euler's compressor principle, determine the temperature rise across the impeller.
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Centrifugal Compressors
Slip factor in a centrifugal compressor accounts for
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Centrifugal Compressors
The degree of reaction in an axial compressor stage is
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Axial Compressors
Stage efficiency of a single-stage axial compressor is defined as
TS PGECET - 2026
TS PGECET
Aerospace Engineering
Axial Compressors
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