Aerospace Engineering GATE 2024 Questions with Answer

Ques 14 Flight Mechanics

Which of the following statements about a general aviation aircraft, while operating at point Q in the V-n diagram, is/are true?

Ques 15 Flight Mechanics

An airplane experiences a net vertical ground reaction of 15000 N during landing. The weight of the airplane is 10000 N. The landing vertical load factor, defined as the ratio of inertial load to the weight of the aircraft, is _______ (rounded off to 1 decimal place).

Ques 16 Flight Mechanics

Which of the following statements about absolute ceiling and service ceiling for a piston-propeller aircraft is/are correct?

Ques 17 Flight Mechanics

For an airplane having directional/weathercock static stability, which of the following options is/are correct?

B

The variation of yawing moment coefficient (C_n) with sideslip angle (β) for the airplane will look like

Ques 18 Flight Mechanics

For an aircraft moving at 4 km altitude above mean sea level at a Mach number of 0.2, the ratio of equivalent airspeed to true airspeed is _______ (rounded off to 2 decimal places).
The density of air at mean sea level is 1.225 kg/m³ and at 4 km altitude is 0.819 kg/m³.

Ques 19 Flight Mechanics

For a general aviation airplane, one of the complex conjugate pairs of eigenvalues for longitudinal dynamics is given by -0.039 ± 0.0567i (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).

Ques 20 Flight Mechanics

An airplane of mass 1000 kg is in steady level flight with a speed of 50 m/s. The wing has an elliptic planform with a span of 20 m and a planform area of 31.4 m². Assuming the density of air at that altitude to be 1 kg/m³ and acceleration due to gravity to be 10 m/s², the induced drag on the wing is _______ N (rounded off to 1 decimal place).

Ques 21 Fluid Mechanics

In the context of steady, inviscid, incompressible flows, consider the superposition of a uniform flow with speed U along the positive x-axis (from left to right), and a source of strength A located at the origin. Which one of the following statements is NOT true regarding the location of the stagnation point of the resulting flow?

Ques 22 Fluid Mechanics

On Day 1, an aircraft flies with a speed of V₁ m/s at an altitude where the temperature is T₁ K. On Day 2, the same aircraft flies with a speed of √1.2 * V₁ m/s at an altitude where the temperature is 1.2 * T₁ K. How does the Mach number M₂ on Day 2 compare with the Mach number M₁ on Day 1? Assume ideal gas behavior for air. Also assume the ratio of specific heats and molecular weight of air to be the same on both days.

Ques 23 Fluid Mechanics

Consider a steady, isentropic, supersonic flow (Mach number M > 1) entering a Convergent-Divergent (CD) duct as shown in the figure. Which one of the following options correctly describes the flow at the throat?

Ques 24 Fluid Mechanics

Consider steady, incompressible, inviscid flow past two airfoils shown in the figure. The coefficient of pressure at the trailing edge of the airfoil with finite angle, shown in figure (I), is C_P1 while that at the trailing edge of the airfoil with cusp, shown in figure (II), is C_PH. Which one of the following options is TRUE?

Ques 25 Fluid Mechanics

Consider a flat plate, with a sharp leading edge, placed in a uniform flow of speed U. The direction of the free-stream flow is aligned with the plate. Assume that the flow is steady, incompressible and laminar. The thickness of the boundary layer at a fixed stream-wise location L from the leading edge of the plate is δ. Which one of the following correctly describes the variation of δ with U?

Ques 26 Fluid Mechanics

Shock structures for flow at three different Mach numbers over a given wedge are shown in the figure below. Assuming that only the weak shock solutions are possible for the attached oblique shocks, which one of the following options is TRUE?