List of top Aeronautical and Aerospace Engineering Questions

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)

In 2D potential flow, the doublet is the limit of the superposition of which two singularities?

An ideal glider has drag characteristics given by \[ C_D = C_{D0} + C_{Di}, \] where \(C_{Di} = K C_L^2\) is the induced drag coefficient, \(C_L\) is the lift coefficient, and \(K\) is a constant. For maximum range of the glider, the ratio \(\dfrac{C_{D0}}{C_{Di}}\) is:

The figures shown in the options are schematics of airfoil shapes (not to scale). For a civilian transport aircraft designed for a cruise Mach number of \(0.8\), which among them is aerodynamically best suited as a wing section?

Consider the Blasius solution for the incompressible laminar flat–plate boundary layer. Among the options, select the correct relation for the development of the momentum thickness \(\theta\) with distance \(x\) from the leading edge along the plate.