List of top Aeronautical and Aerospace Engineering Questions

The shape functions indicated here are for a
Shear flow has the same units as
Axisymmetric problems involving axisymmetric loading and solids of revolution can be conveniently formulated with the following element type.
Which of the following statements is true about Finite Element Analysis (FEA)?
Which of these analyses needs a stretched grid?
The lifting flow over circular cylinder is obtained by the combination of
Which one of the following is not an example of an adapted nozzle?
For which of these applications is the turbo shaft engine most suited?
When a nozzle is said to be over expanded?
Which of the following is usually measured as the angle between the line of 25% chord and a perpendicular to the root chord?
Which of the following is a barotropic flow?
Numerical panel methods are applicable for
The schadowgraph flow visualization technique depends on
What is the purpose of a fuel injection system in the combustor?
The ratio of modulus of rigidity to bulk modulus for a Poisson's ratio of 0.25 would be:
Flow separation is due to
Which type of grids is the best for flow over an airfoil?
What is the center pressure if the lift coefficient and lift curve slope of an aerofoil of percentage camber 0.6 are 1.02 and 2, respectively?
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)
A general aviation airplane has $W=10 \,\text{kN}$, $S=15 \,\text{m}^2$, $\rho=0.60 \,\text{kg/m}^3$, $C_{D0}=0.025$, $K=0.05$, thrust $T=1 \,\text{kN}$. Find the maximum cruise speed.
Airplane A and Airplane B are cruising at altitudes of \(2~\mathrm{km}\) and \(4~\mathrm{km}\), respectively. The free–stream density and static pressure at \(2~\mathrm{km}\) are \(1.01~\mathrm{kg/m^3}\) and \(79.50~\mathrm{kPa}\); at \(4~\mathrm{km}\) they are \(0.82~\mathrm{kg/m^3}\) and \(61.70~\mathrm{kPa}\). The differential pressure reading from the pitot–static tubes is \(3~\mathrm{kPa}\) for both airplanes. Assuming incompressible flow, the ratio of cruise speeds \(V_A/V_B\) is \underline{\hspace{1cm}}. \;(round off to two decimal places)