Step 1: Drag deceleration model.
For a ballistic entry (no lift guidance), the magnitude of drag deceleration is
\[
\left|\frac{dV}{dt}\right| \;\approx\; \frac{D}{m}
= \frac{1}{2}\,\frac{\rho V^2 C_D A}{m}
= \frac{\rho V^2}{2\,\beta},
\]
where \(\rho(h)\) is air density, \(V\) is speed, and \(\beta=\dfrac{m}{C_D A}\) is the ballistic coefficient (constant for a given vehicle/attitude).
Step 2: Competing trends during entry.
- \(\rho(h)\): increases rapidly as altitude decreases (roughly \(\rho \propto e^{-h/H}\) with scale height \(H\)).
- \(V\): starts very large at high \(h\) and decreases due to drag as the vehicle descends.
Thus \(|dV/dt| \propto \rho V^2\) is the product of an increasing factor \(\rho(h)\) and a decreasing factor \(V^2(h)\).
Step 3: Location of the maximum.
At very high \(h\): \(\rho\) is tiny \(\Rightarrow |dV/dt|\) small despite large \(V\).
As \(h\) decreases: \(\rho\) grows quickly while \(V\) is still high \(\Rightarrow |dV/dt|\) increases.
Deeper down: \(V\) has dropped substantially (large energy already dissipated) even though \(\rho\) is higher \(\Rightarrow\) the product \(\rho V^2\) reaches a maximum (the "max-\(q\)"/max-deceleration region) and then decreases.
Therefore the qualitative curve must be bell-shaped: small at high altitude, increasing to a peak at mid–altitudes, and falling again toward lower altitudes.
Step 4: Eliminate wrong plots.
(A) and (C) show large deceleration at high altitude—contradicts tiny \(\rho\).
(B) shows deceleration growing toward the ground monotonically—ignores the strong reduction in \(V\).
(D) matches the expected peak at an intermediate \(h\).
Final Answer:
\[
\boxed{\text{(D) Bell-shaped }|dV/dt|\text{ vs. }h\text{ with a peak at mid-altitude}}
\]
F and G denote two points on a spacecraft’s orbit around a planet, as indicated in the figure. O is the center of the planet, P is the periapsis, and the angles are as indicated in the figure. If \( OF = 8000 \, {km} \), \( OG = 10000 \, {km} \), \( \theta_F = 0^\circ \), and \( \theta_G = 60^\circ \), the eccentricity of the spacecraft's orbit is __________ (rounded off to two decimal places).
F and G denote two points on a spacecraft’s orbit around a planet, as indicated in the figure. O is the center of the planet, P is the periapsis, and the angles are as indicated in the figure. If \( OF = 8000 \, {km} \), \( OG = 10000 \, {km} \), \( \theta_F = 0^\circ \), and \( \theta_G = 60^\circ \), the eccentricity of the spacecraft's orbit is ___________ (rounded off to two decimal places).

Two designs A and B, shown in the figure, are proposed for a thin-walled closed section that is expected to carry only torque. Both A and B have a semi-circular nose, and are made of the same material with a wall thickness of 1 mm. With strength as the only criterion for failure, the ratio of maximum torque that B can support to the maximum torque that A can support is _________ (rounded off to two decimal places).
A thin flat plate is subjected to the following stresses: \[ \sigma_{xx} = 160 \, {MPa}; \, \sigma_{yy} = 40 \, {MPa}; \, \tau_{xy} = 80 \, {MPa}. \] Factor of safety is defined as the ratio of the yield stress to the applied stress. The yield stress of the material under uniaxial tensile load is 250 MPa. The factor of safety for the plate assuming that material failure is governed by the von Mises criterion is _________ (rounded off to two decimal places).
A prismatic vertical column of cross-section \( a \times 0.5a \) and length \( l \) is rigidly fixed at the bottom and free at the top. A compressive force \( P \) is applied along the centroidal axis at the top surface. The Young’s modulus of the material is 200 GPa and the uniaxial yield stress is 400 MPa. If the critical value of \( P \) for yielding and for buckling of the column are equal, the value of \( \frac{l}{a} \) is __________ (rounded off to one decimal place).
A uniform rigid bar of mass 3 kg is hinged at point F, and supported by a spring of stiffness \( k = 100 \, {N/m} \), as shown in the figure. The natural frequency of free vibration of the system is ___________ rad/s (answer in integer).
A jet-powered airplane is steadily climbing at a rate of 10 m/s. The air density is 0.8 kg/m³, and the thrust force is aligned with the flight path. Using the information provided in the table below, the airplane’s thrust to weight ratio is ___________ (rounded off to one decimal place). 