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Aeronautical and Aerospace Engineering
List of top Aeronautical and Aerospace Engineering Questions
A positively cambered airfoil is placed in a uniform flow (velocity, \( U_\infty \)) at its zero-lift angle of attack. \( M \) is the corresponding pitching moment. Which one of the following representations accurately describes this scenario?
GATE AE - 2025
GATE AE
Aeronautical and Aerospace Engineering
Airfoil Theory
Potential function for three dimensional doublet of strength \( \mu \) is
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Fluid flow
The shear centre position of a thin-walled symmetrical channel section will lie
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Shear Centre
The physical principle used for the derivation of momentum equation is
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Fluid flow
The ratio of modulus of rigidity to bulk modulus for a Poisson's ratio of 0.25 would be:
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Stresses in Beams
Which of the following states that the time rate of change of circulation around a closed curve consisting of the same fluid elements is zero?
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Fluid flow
Shear flow has the same units as
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Shear Centre
A rectangular section beam subjected to a bending moment M varying along its length is required to develop the same maximum bending stress at any cross section. If the depth of the section is constant, then its width will vary as:
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Stresses in Beams
Which of these analyses needs a stretched grid?
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Fluid Dynamics
Which of the following assumptions / statements is NOT true about the Euler-Bernoulli beam theory?
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Stresses in Beams
AB = 40 cm while BC = 30 cm. Areas A and C are equal to 8 \( \text{cm}^2 \) while areas B and D are 6 \( \text{cm}^2 \). The given section is subject to \( M_x = 100 \text{kNm} \) and \( M_y = 40 \text{kNm} \). Find an expression for the bending stress. Assume that the webs are ineffective in bending.
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Stresses in Beams
Numerical panel methods are applicable for
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Fluid Dynamics
In a short column with eccentric loading, the neutral axis:
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Columns and Biaxial Stress System
If a laminate consists of pairs of layers with identical thickness and elastic properties, but with orientation of +θ and -θ with respect to the laminate reference axis, then the laminate is called as
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Composite Materials
Which type of grids is the best for flow over an airfoil?
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Fluid Dynamics
The Shear stresses in the fiber and matrix are 200GPa and 20GPa respectively. If the fiber volume fraction is 70%, then the longitudinal compressive strength of the lamina is
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Composite Materials
Which of the following statements is NOT true of a 1-D problem represented using 2-node line elements as indicated?
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Finite Element Methods
If two shafts of same length, one of which is hollow, transmit equal torque and have equal maximum shear stress, then they should have equal
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Torsion
The shape functions indicated here are for a
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Finite Element Methods
Ram efficiency is defined as
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Heat Transfer
Axisymmetric problems involving axisymmetric loading and solids of revolution can be conveniently formulated with the following element type.
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Finite Element Methods
Consider an equal-leg angle section cantilever beam subject to a vertical shearing load at the tip where the line of action of the applied vertical force passes through the centroid. This beam will experience
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Bending
Which of the following statements is true about Finite Element Analysis (FEA)?
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Finite Element Methods
The lifting flow over circular cylinder is obtained by the combination of
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Airfoil Theory
For a given rotational speed of a rotor of an axial flow compressor, as the fan tip radius increases, the centrifugal stress on the fan blade
TANCET - 2024
TANCET
Aeronautical and Aerospace Engineering
Air and Gas Compressors
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