GATE AE 2024 Question Paper & Solutions

Verbal Aptitude

If '→' denotes increasing order of intensity, then the meaning of the words [dry → arid → parched] is analogous to [diet → fast → ________ ]. Which one of the given options is appropriate to fill the blank?

Quantitative Aptitude

If two distinct non-zero real variables x and y are such that (x + y) is proportional to (x - y) then the value of x y

Quantitative Aptitude

Consider the following sample of numbers: 9, 18, 11, 14, 15, 17, 10, 69, 11, 13 The median of the sample is

Quantitative Aptitude

The number of coins of ₹1, ₹5, and ₹10 denominations that a person has are in the ratio 5:3:13. Of the total amount, the percentage of money in ₹5 coins is

Quantitative Aptitude

For positive non-zero real variables p and q, if log (p^2 + q^2) = log p + log q + 2 log 3 , then, the value of p4+q4 p2q2 is

Quantitative Aptitude

In the given text, the blanks are numbered (i)-(iv). Select the best match for all the blanks. Steve was advised to keep his head (i) before heading (ii) to bat; for, while he had a head (iii) batting, he could only do so with a cool head s (iv) his shoulders.

Analytical & Spatial Aptitude

A rectangular paper sheet of dimensions 54 cm × 4 cm is taken. The two longer edges of the sheet are joined together to create a cylindrical tube. A cube whose surface area is equal to the area of the sheet is also taken. Then, the ratio of the volume of the cylindrical tube to the volume of the cube is

Quantitative Aptitude

The pie chart presents the percentage contribution of different macronutrients to a typical 2,000 kcal diet of a person. The typical energy density (kcal/g) of these macronutrients is given in the table. Macronutrient Energy density (kcal/g) Carbohydrates 4 Proteins 4 Unsaturated fat 9 Saturated fat 9 Trans fat 9 The total fat (all three types), in grams, this person consumes is

Analytical & Spatial Aptitude

A rectangular paper of 20 cm × 8 cm is folded 3 times. Each fold is made along the line of symmetry, which is perpendicular to its long edge. The perimeter of the final folded sheet (in cm) is

Quantitative Aptitude

The least number of squares to be added in the figure to make AB a line of symmetry is

Linear Algebra

The following system of linear equations 7x - 3y + z = 0 3x - y + z = 0 x - y - z = 0 has:

Differential Equations

The acceleration of a body travelling in a straight line is given by $a = -C_1 - C_2 v^2$, where $v$ is the velocity, and $C_1, C_2$ are positive constants. Starting with an initial positive velocity $v_0$, the distance travelled by the body before coming to rest for the first time is:

Aerospace Materials & Fatigue

The three-dimensional stress-strain relationship for an isotropic material is given as { $\sigma$xx $\sigma$yy $\sigma$zz $\tau$yz $\tau$xz $\tau$xy} = [ P Q Q Q P Q Q Q P 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 R 0 0 0 R 0 0 0 R] { 𝜀xx 𝜀yy 𝜀zz $\gamma$yz $\gamma$xz $\gamma$xy} where, $P, Q$ and $R$ are the three elastic constants, $\sigma$ and $\tau$ represent normal and shear stresses and 𝜀 and $\gamma$ represent normal and engineering shear strains. Which one of the following options is correct?

Structural Dynamics & Aeroelasticity

Consider the free vibration responses P, Q, R and S (shown in the figure) of a single degree of freedom spring-mass-damper system with the same initial conditions. For the different damping cases listed below, which one of the following options is correct? 1. Overdamped 2. Underdamped 3. Critically damped 4. Undamped

Numerical Methods

For a single degree of freedom spring-mass-damper system subjected to harmonic forcing, the part of the motion (response) that decays due to damping is known as:

Thermodynamic Cycles of Gas Turbines

For an ideal gas, the specific heat at constant pressure is 1147 J/kg K and the ratio of specific heats is equal to 1.33. What is the value of the gas constant for this gas in J/kg K?

Inlets, Combustors & Nozzles

A surrogate liquid hydrocarbon fuel, approximated as C 10H12, is being burned in a land-based gas turbine combustor with dry air (79% N 2 and 21% O 2 by volume). How many moles of dry air are required for the stoichiometric combustion of the surrogate fuel with dry air at atmospheric temperature and pressure?

Thermodynamic Cycles of Gas Turbines

In the figure shown below, various thermodynamics processes for a n ideal gas are represented. Match each curve with the process that it best represents.

Inlets, Combustors & Nozzles

In an airbreathing gas turbine engine, the combustor inlet temperature is 600 K. The heating value of the fuel is 43.4 × 106 J/kg. Assume Cp to be 1100 J/kg K for air and burned gases, and fuel-air ratio f << 1.0. Neglect kinetic energy at the inlet and exit of the combustor and assume 100% burner efficiency . What is the fuel -air ratio required to achieve 1300 K temperature at the combustor exit?

Atmospheric Flight Mechanics

Which one of the following figures represents the drag polar of a general aviation aircraft?

Basic 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 $\Lambda$ located at the origin. Which one of the following statements is NOT true regarding the location of the stagnation point of the resulting flow?

Compressible Flow & Shocks

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 the days.

Compressible Flow & Shocks

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?

Airfoil & Wing Theory

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 CPI while that at the trailing edge of the airfoil with cusp, shown in figure (II), is CPII. Which one of the following options is TRUE?

Aerospace Materials & Fatigue

Which of the following options is/are correct?

Space Dynamics & Orbital Mechanics

Which of the following statements is/are correct about a satellite moving in a geostationary orbit?

Static Stability & Control

In a conventional configuration airplane, the rudder can be used:

Atmospheric 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?

Calculus

Two fair dice with numbered faces are rolled together. The faces are numbered from 1 to 6. The probability of getting odd numbers on both the dice is ________________ (rounded off to 2 decimal places).

Rocket Propulsion

A particle acted upon by a constant force 4î + ĵ - 3k̂ N is displaced from point A with position vector î + 2ĵ + 3k̂ m to point B with position vector 5î + 4ĵ + k̂ m. The work done by this force is _______ J (answer in integer).

Numerical Methods

Using Trapezoidal rule with one interval, the approximate value of the definite integral: ∫ dx 1 + x2 2 1 = ______ (rounded off to 2 decimal places).

Strength of Materials & Elasticity

A material has Poisson's ratio $\nu$ = 0.5 and Young's modulus E=2500 MPa. The percentage change in its volume when subjected to a hydrostatic stress of magnitude 10 MPa is ______ (answer in integer).

Atmospheric 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).

Inlets, Combustors & Nozzles

An aircraft with a turbojet engine is flying with 250 m/s speed at an altitude, where the density of air is 1 kg/m^3. The inlet area of the engine is 1 m^2. The average velocity of the exhaust gases at the exit of the nozzle, with respect to aircraft, is 550 m/s. Assume the engine exit pressure is equal to the ambient pressure and the fuel-air ratio is negligible. The uninstalled thrust produced by the engine at these conditions is _________ N (rounded off to the nearest integer).

Airfoil & Wing Theory

Using thin airfoil theory, the lift coefficient of a NACA 0012 airfoil placed at 5 o angle of attack in a uniform flow is _____________ (rounded off to 2 decimal places).

Linear Algebra

Given y = epx sin qx, where p and q are non-zero real numbers, the value of the differential expression $\frac{d^2y}{dx^2}$ - 2p $\frac{dy}{dx}$ + (p^2 + q^2)y is

Calculus

The volume of the solid formed by a complete rotation of the shaded portion of the circle of radius R about the y-axis is k$\pi$R^3. The value of k is:

Atmospheric Flight Mechanics

As per the International Standard Atmosphere model, which one of the following options about density variation with increase in altitude in the isothermal layer is correct?

Differential Equations

At a point in the trajectory of an unpowered space vehicle moving about the Earth, the altitude above the mean sea level is 600 km , and the speed with reference to a coordinate system fixed to the center of mass of the Earth is 9 km/s. Assume that the Earth is a sphere with a radius 6400 km and GMEartℎ = 3.98 × 1014 m^3/s^2, where, G is the universal gravitational constant and MEartℎ is mass of the Earth. The trajectory is:

Compressors and Turbines

A multistage axial compressor, with overall isentropic efficiency of 0.83, is used to compress air at a stagnation temperature of 300 K through a pressure ratio of 10:1. Each stage of the compressor is similar, and the stagnation temperature rise across each compressor stage is 20 K. Assume Cp = 1005 J/kg K and  = 1.4 for air. How many stages are there in the compressor?

Thermodynamic Cycles of Gas Turbines

An aircraft with a turbojet engine is flying at 250 m/s. The uninstalled thrust produced by the engine is 60000 N. The heating value of the fuel is 44 × 10 6 J/kg. The engine has a thermal efficiency of 35% while burning the fuel at a rate of 3 kg/s. Assume the engine exit pressure to be equal to the ambient pressure. What is the propulsion efficiency of the engine under these conditions (in percentage)?

Basic 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 $\delta$. Which one of the following correctly describes the variation of $\delta$ with U?

Compressible Flow & Shocks

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?

Compressible Flow & Shocks

Air flowing at Mach number M = 2 from left to right accelerates to M = 3 across an expansion corner as shown in the figure. What is the value of $\delta$ (the angle between the Forward and Rearward Mach lines) in degrees? The values of the Prandtl-Meyer functions are $\nu$(3) = 49.76o and $\nu$(2) = 26.38o.

Calculus

Consider the function f(x) = {x2 for x < 0 x for x ≥ 0 where x is real. Which of the following statements is/are correct?

Aerospace Materials & Fatigue

The figure shows plots of two yield loci for an isotropic material, where $\sigma$I and $\sigma$II are the principal stresses, and $\sigma$Y is the yield stress in uniaxial tension. Which of the following statements is/are correct?

Atmospheric Flight Mechanics

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

Static Stability & Control

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

Inlets, Combustors & Nozzles

Which of the following statements is/are TRUE for an axial turbine?

Compressors and Turbines

Which of the following statements is/are TRUE for a single stage axial compressor?

Linear Algebra

Consider the matrix A = [5 -4 k -1], where k is a constant. If the determinant of A is 3, then the ratio of the largest eigenvalue of A to the constant k is ___________ (rounded off to 1 decimal place).

Strength of Materials & Elasticity

The state of stress at a point is caused by two separate loading cases. One of them produces a pure uniaxial tension along the x′ direction, and other one produces a pure uniaxial compression along the y′ direction, as shown in the figure. The sum of maximum and minimum principal stresses for the resultant state of stress caused by both loads acting simultaneously is ___________ N/mm 2 (rounded off to 1 decimal place).

Compressors and Turbines

In the figure shown below, the magnitude of internal force in member BC is ___________ N (rounded off to 1 decimal place).

Thin-Walled Structures

The cross section of a thin-walled beam with uniform wall thickness t, shown in the figure, is subjected to a bending moment Mx = 10 Nm. If h = 1 m and t = 0.00 1 m, the magnitude of maximum normal stress in the cross section is _________N/m^2 (answer in integer).

Inlets, Combustors & Nozzles

The equations of motion for a two degrees of freedom undamped spring -mass system are: mẍ1 + 2kx1 - kx2 = 0 mẍ2 - kx1 + 2kx2 = 0 where m and k represent mass and stiffness respectively, in corresponding SI units, and x1 and x2 are the degrees of freedom. The larger of the two natural frequencies is given by: $\omega$ = $\alpha$√ k m rad/s. The value of $\alpha$ is ________ (rounded off to 2 decimal places).

Strength of Materials & Elasticity

Consider the plane strain field given by 𝜀xx = 10 xy2, 𝜀yy = -5 x2y and $\gamma$xy = A xy (2x - y) where, A is a constant and $\gamma$xy is the engineering shear strain . The value of the constant A for the strain field to be compatible is _____________ (rounded off to 1 decimal place).

Rocket Propulsion

A chemical rocket with an ideally expanded flow through the nozzle produces 5 × 106 N thrust at sea level. The specific impulse of the rocket is 200 s and acceleration due to gravity at the sea level is 9.8 m/s^2. The propellent mass flow rate out of the rocket nozzle is _________ kg/s (rounded off to the nearest integer).

Compressors and Turbines

A centrifugal compressor is designed to operate with air. At the leading edge of the tip of the inducer (eye of the impeller), the blade angle is 45o, and the relative Mach number is 1.0. The stagnation temperature of the incoming air is 300 K. Consider  = 1.4. Neglect pre-whirl and slip. The inducer tip speed is ________ m/s (rounded off to the nearest integer).

Compressible Flow & Shocks

Consider the following Fanno flow problem: Flow enters a constant area duct at a temperature of 273 K and a Mach number 0.2 and eventually reaches sonic condition (Mach number =1) due to friction. Assume $\gamma$ = 1.4. The static temperature at the location where sonic condition is reached is_____________ K (rounded off to 2 decimal places).

Space Dynamics & Orbital Mechanics

Consider an artificial satellite moving around the Moon in an elliptic orbit. The altitude of the satellite from the Moon's surface at the perigee is 25 km and that at the apogee is 134 km. Assume the Moon to be spherical with a radius of 1737 km. The trajectory is considered with reference to a coordinate system fixed to the center of mass of the Moon. The ratio of the speed of the satellite at the perigee to th at at the apogee is ___________ (rounded off to 2 decimal places).

Compressible Flow & Shocks

For an aircraft moving at 4 km altitude above mean sea level at a Mach number of 0.2, the ratio of equivalent air speed to true air speed 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/m^3.

Linear Algebra

For a general aviation airplane, one of the complex conjugate pair of eigenvalues for longitudinal dynamics is given by -0.039 ± 0.0567 i (in SI units) . If the system is disturb ed 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).

Airfoil & Wing Theory

The figure (not to scale) shows a control volume to estimate the forces on the airfoil with elliptic cross-section. Surfaces 2 and 3 are streamlines. Velocity profiles are measured at the upstream end (surface 1) and at the downstream end (surface 4) of the control volume. The drag coefficient for the airfoil is defined as Cd = D 1 2 $\rho$ U∞ 2 c , where D is the drag force on the airfoil per unit span and  is the density of the air. The static pressure, p , is constant over the entire surface of the control volume. Assuming the flow to be incompressible, two -dimensional and steady, the Cd for the airfoil is _________ (rounded off to 3 decimal places).

Airfoil & Wing Theory

An airplane of mass 1000 kg is in a steady level flight with a speed of 50 m/s. The wing has an elliptic planform with a span of 20 m and planform area 31.4 m^2. Assuming the density of air at that altitude to be 1 kg/m 3 and acceleration due to gravity to be 10 m/s^2, the induced drag on the wing is _________ N (rounded off to 1 decimal place).

Aerospace Materials & Fatigue

It is desired to estimate the aerodynamic drag, D, on a car traveling at a speed of 30 m/s. A one-third scale model of the car is tested in a wind -tunnel following the principles of dynamic similarity. The drag on the scaled model is measured to be Dm. The ratio D/Dm is _________ (rounded off to 1 decimal place).