List of top Flight Mechanics Questions asked in GATE Aerospace Engineering

For a general aviation airplane, one of the complex conjugate pair of eigenvalues for longitudinal dynamics is given by $\lambda = -0.039 \pm 0.0567 i$ (in SI units). If the system is disturbed to excite only this mode, the time taken for the amplitude of response to become half in magnitude is ............ s (rounded off to 1 decimal place).

An airplane with wing planform area $S=20\,\text{m}^2$ and weight $W=8\,\text{kN}$ is flying straight and level with a speed of $V=100\,\text{m/s}$. The total drag coefficient is $C_D=0.026$ and the air density is $\rho=0.7\,\text{kg/m}^3$. The total thrust required to introduce a steady climb at angle $\gamma=0.1$ radians is ............. N. (round off to the nearest integer)

The maximum permissible load factor and the maximum lift coefficient for an airplane are $n_{\max}=7$ and $C_{L,\max}=2$, respectively. For a wing loading $W/S=6500\ \text{N/m}^2$ and air density $\rho=1.23\ \text{kg/m}^3$, the speed yielding the highest possible turn rate in the vertical plane is .............. m/s. (round off to the nearest integer)

An airplane weighing \(40\ \text{kN}\) is landing on a horizontal runway and is retarded by an arresting cable. The tension in the arresting cable at a given instant is \(100\ \text{kN}\), and the cable makes \(10^\circ\) with the runway as shown. Assume engine thrust continues to balance airplane drag. The magnitude of the horizontal load factor is \underline{\hspace{1cm}}. \;(round off to one decimal place) \begin{center} \includegraphics[width=0.5\textwidth]{09.jpeg} \end{center}

For a longitudinally statically stable aircraft, which one of the following represents the relationship between the coefficient of pitching moment about the center of gravity \(C_{m_{cg}}\) and absolute angle of attack \(\alpha_a\)? (Note: nose–up moment is positive.)

Consider a thin symmetric airfoil at a 2 degree angle of attack in a uniform flow at 50 m/s. The pitching moment coefficient about its leading edge is _________ (rounded off to three decimal places).

For a conventional airplane in straight, level, constant velocity flight condition, which of the following condition(s) is/are possible on Euler angles (\(\phi, \theta, \psi\)), angle of attack (\(\alpha\)) and the sideslip angle (\(\beta\))?

An unpowered glider is flying at a glide angle of 10 degrees. Its lift-to-drag ratio is _________ (round off to two decimal places).

For International Standard Atmosphere (ISA) up to 11 km, which of the following statement(s) is/are true?

The service ceiling of an airplane is the altitude

Regarding the horizontal tail of a conventional airplane, which one of the following statements is true?