List of top Aeronautical and Aerospace Engineering Questions

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
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
Which of the following statements is NOT true of a 1-D problem represented using 2-node line elements as indicated?
The shear centre position of a thin-walled symmetrical channel section will lie
The shape functions indicated here are for a
Axisymmetric problems involving axisymmetric loading and solids of revolution can be conveniently formulated with the following element type.
Shear flow has the same units as
Which of the following statements is true about Finite Element Analysis (FEA)?
The semi-span of a rectangular wing of plan form area 8.4 m² is 3.5 m. The aspect ratio of the wing is
The lifting flow over circular cylinder is obtained by the combination of
When a nozzle is said to be over expanded?
The physical principle used for the derivation of momentum equation is
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?
Which of these analyses needs a stretched grid?
Which of the following is usually measured as the angle between the line of 25% chord and a perpendicular to the root chord?
In the subcritical operation mode of a supersonic inlet, shock strands
Pressure gradient in the flow direction
The schadowgraph flow visualization technique depends on
Numerical panel methods are applicable for
Flow separation is due to
Consider the International Standard Atmosphere (ISA) with $h$ being the geopotential altitude (in km) and $\dfrac{dT}{dh}$ being the temperature gradient (in K/m). Which of the following combination(s) of $\Big(h, \dfrac{dT}{dh}\Big)$ is/are correct as per ISA?
A thin cambered airfoil has lift coefficient $C_l=0$ at angle of attack $\alpha=-1^\circ$. Estimate $C_l$ at $\alpha=4^\circ$, assuming stall occurs at much higher $\alpha$. (round off to two decimal places)
The operating characteristics of a pump are measured as $C_p = a \Phi^2$, where \[ C_p = \frac{P}{\rho \omega^3 D^5}, \Phi = \text{flow coefficient}, a=\text{constant}. \] If $\omega$ increases by 25% (i.e. $\omega \to 1.25\omega$) and the flow coefficient $\Phi$ is constant, determine $\alpha$ such that $P$ becomes $\alpha P$. (round off to two decimal places)
In potential flow, a uniform stream of strength $U$ flows along x-axis. Line sources of strength $\pi/2, -\pi/3, \pi/4, -\pi/5$ are placed at $x=0,1,2,3$ respectively. Find strength of an additional line source at $x=4$ such that a closed streamline encircles all five sources. (round off to two decimal places)
Enstrophy is defined as square of magnitude of vorticity. For velocity field \[ \vec{V} = (4x - 1.5y + 2.5z)\hat{i} + (1.5x - 1.5y)\hat{j} + (0.7xy)\hat{k}, \] find enstrophy at $(1,1,1)$. (round off to two decimal places)