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?

In steady, inviscid, incompressible flow, superpose a uniform stream of speed $U$ along $+x$ (left $\to$ right) with a source of strength $\Lambda$ at the origin. Which statement about the stagnation point's location is NOT true?

Day 1: speed $V_1$ at temperature $T_1$ K. Day 2: speed $\sqrt{1.2}\,V_1$ at temperature $1.2\,T_1$ K. For air treated as an ideal gas with the same $\gamma$ and $R$ both days, compare Mach numbers $M_2$ (Day 2) and $M_1$ (Day 1).

Steady, incompressible, inviscid flow past two airfoils is shown. The pressure coefficient at the trailing edge of (I) with a finite included angle is $C_{pI}$; for (II) with a cusp (zero included angle) it is $C_{pII}$. Which statement is TRUE?

As per the International Standard Atmosphere (ISA), which statement about density variation with altitude in an isothermal layer is correct?

The figure shows a control volume to estimate drag on an airfoil with elliptic cross-section. Surfaces 2 and 3 are streamlines. Velocity is measured at upstream (surface 1) and downstream (surface 4). The drag coefficient is $C_d = \tfrac{D{\tfrac{1}{2} \rho U_\infty^2 c}$, where $D$ is drag force per unit span, $\rho$ is density, $U_\infty$ is free-stream velocity, and $c$ is chord. The static pressure is constant over the control surface. Flow is incompressible, 2D, steady. Find $C_d$ (rounded to 3 decimals).} \begin{center} \includegraphics[width=0.7\textwidth]{18.jpeg} \end{center}

Consider the following Fanno flow problem: Flow enters a constant area duct at a temperature of 273 K and a Mach number 0.2 and eventually reaches sonic condition (Mach number = 1) due to friction. Assume $\gamma = 1.4$. The static temperature at the location where sonic condition is reached is ................. K (rounded off to 2 decimal places).

Using thin airfoil theory, find the lift coefficient of a NACA 0012 airfoil at $\alpha=5^\circ$ in uniform flow (rounded to 2 decimal places).

Potential function for three dimensional doublet of strength $ \mu $ is

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

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

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

The deflection of the free end of a cantilever beam subjected to a concentrated load at its mid span is given by:

The function $ y = A \left(1 - \cos\left(\frac{2\pi x}{L}\right)\right) $ is an allowed approximate function for a

Modified Tsai-Hill theory

A closely coiled helical spring has a stiffness of 8N/mm. If it extends by 5 mm, the energy absorbed is

The stress due to suddenly applied load is _______ compared to that of the gradually applied load?