Which one of the following figures represents the drag polar of a general aviation aircraft? (Axes: vertical \(C_L\), horizontal \(C_D\)).

Remember \(C_D=C_{D0}+kC_L^2\). If the graph's axes swap roles (plotting \(C_L\) vs \(C_D\)), the usual "upward" parabola becomes a "right-opening" one with vertex at \(C_{D0}\).
Step 1: Drag polar for aircraft.
For typical subsonic aircraft, \[ C_D=C_{D0}+k\,C_L^{\,2}\quad (k > 0). \] This is a parabola in the \(C_D\)-\(C_L\) plane with minimum drag \(C_{D0}\) at \(C_L=0\).
Step 2: Plotting with given axes (\(y=C_L,\ x=C_D\)).
Solving for \(C_L\) gives \[ C_L=\pm \sqrt{\frac{C_D-C_{D0}}{k}}, \] which is a sideways-opening} parabola to the right, vertex at \((C_{D0},0)\), symmetric about \(C_L=0\). This matches the sketch in option (D).
\[\boxed{\text{Option (D) — sideways-opening parabolic polar}}\]
An ideal ramjet with an optimally expanded exhaust is travelling at Mach 3. The ambient temperature and pressure are 260 K and 60 kPa, respectively. The inlet air mass flow rate is 50 kg/s. Exit temperature of the exhaust gases is 700 K. Fuel mass flow rate is negligible compared to air mass flow rate. Gas constant is \( R = 287 \, {J/kg/K} \), and specific heat ratio is \( \gamma = 1.4 \). The thrust generated by the engine is __________ kN (rounded off to one decimal place).
A monopropellant liquid rocket engine has 800 injectors of diameter 4 mm each, and with a discharge coefficient of 0.65. The liquid propellant of density 1000 kg/m³ flows through the injectors. There is a pressure difference of 10 bar across the injectors. The specific impulse of the rocket is 1500 m/s. The thrust generated by the rocket is __________ kN (rounded off to one decimal place).