MCQOPTIONS
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MCQOPTIONS
This section includes 102 Mcqs, each offering curated multiple-choice questions to sharpen your Graduate Aptitude Test (GATE) knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
The primary goal of the financial management is ____________. |
| A. | to maximize the return |
| B. | to minimize the risk |
| C. | to maximize the wealth of owners |
| D. | to maximize profit |
| Answer» E. | |
| 2. |
The least important measure for reducing cost of site development is |
| A. | Clustering the units |
| B. | Eliminating landscaping costs |
| C. | Reducing road lengths |
| D. | All of the Above |
| Answer» E. | |
| 3. |
Pan evaporation data recorded at a certain location over a period of one week are 4.0, 4.3, 4.6, 4.9, 5.12, 5.18, and 6.21 mm. If irrigation scheduling based on ratio of irrigation water (IW) to cumulative pan evaporation (CPE) is practiced, the depth of irrigation at an interval of a week for IW/CPE = 0.9 is |
| A. | 3.60 |
| B. | 4.41 |
| C. | 5.59 |
| D. | 30.88 |
| Answer» E. | |
| 4. |
The rear furrow wheel in a tractor mounted disc plough is provided to |
| A. | reduce the frictional power loss |
| B. | maintain the uniform depth of cut |
| C. | reduce the side draft |
| D. | improve the penetration of the plough |
| Answer» D. improve the penetration of the plough | |
| 5. |
The maximum thickness to chord ratio for the NACA 24012 airfoil is |
| A. | 0.01 |
| B. | 0.12 |
| C. | 0.24 |
| D. | 0.40 |
| Answer» C. 0.24 | |
| 6. |
The parameters that remain constant in a cruise-climb of an aircraft are |
| A. | equivalent airspeed and lift coefficient |
| B. | altitude and lift coefficient |
| C. | equivalent airspeed and altitude |
| D. | lift coefficient and aircraft mass |
| Answer» B. altitude and lift coefficient | |
| 7. |
The drag of an aircraft in steady climbing flight at a given forward speed is |
| A. | inversely proportional to climb angle |
| B. | higher than drag in steady level flight at the same forward speed |
| C. | lower than drag in steady level flight at the same forward speed |
| D. | independent of climb angle |
| Answer» D. independent of climb angle | |
| 8. |
The service ceiling of a transport aircraft is defined as the altitude |
| A. | that is halfway between sea-level and absolute ceiling |
| B. | at which it can cruise with one engine operational |
| C. | at which its maximum rate of climb is zero |
| D. | at which its maximum rate of climb is 0.508 m/s |
| Answer» E. | |
| 9. |
To transfer a satellite from an elliptical orbit to a circular orbit having radius equal to the apogee distance of the elliptical orbit, the speed of the satellite should be |
| A. | increased at the apogee |
| B. | decreased at the apogee |
| C. | increased at the perigee |
| D. | decreased at the perigee |
| Answer» B. decreased at the apogee | |
| 10. |
A circular cylinder is placed in an uniform stream of ideal fluid with its axis normal to the flow. Relative to the forward stagnation point, the angular positions along the circumference where the speed along the surface of the cylinder is equal to the free stream speed are |
| A. | 30, 150, 210 and 330 degrees |
| B. | 45, 135, 225 and 315 degrees |
| C. | 0, 90, 180 and 270 degrees |
| D. | 60, 120, 240 and 300 degrees |
| Answer» B. 45, 135, 225 and 315 degrees | |
| 11. |
Which one of the following values is nearer to the vacuum specific impulse of a rocket engine using liquid hydrogen and liquid oxygen as propellants? |
| A. | 49 sec |
| B. | 450 sec |
| C. | 6000 sec |
| D. | 40000 sec |
| Answer» C. 6000 sec | |
| 12. |
The purpose of a fuel injection system in the combustor is |
| A. | to accelerate the flow in the combustor |
| B. | to increase the stagnation pressure of the fuel-air mixture |
| C. | to ignite the fuel-air mixture |
| D. | to convert the bulk fuel into tiny droplets |
| Answer» E. | |
| 13. |
The diffuser of an airplane engine decelerates the airflow from the flight Mach number 0.85 to the compressor inlet Mach number 0.38. Assume that the ratio of the specific heats is constant and equal to 1.4. If the diffuser pressure recoveiy ratio is 0.92, then the isentropic efficiency of the diffuser is |
| A. | 0.631 |
| B. | 0.814 |
| C. | 0.892 |
| D. | 1.343 |
| Answer» C. 0.892 | |
| 14. |
A gas turbine engine operates with a constant area duct combustor with inlet and outlet stagnation temperatures 540 K and 1104 K respectively. Assume that the flow is one dimensional, incompressible and frictionless and that the heat addition is driving the flow inside the combustor. The pressure loss factor (stagnation pressure loss non-dimensionalized by the inlet dynamic pressure) of the combustor is |
| A. | 0 |
| B. | .0.489 |
| C. | 1.044 |
| D. | 2.044 |
| Answer» B. .0.489 | |
| 15. |
At a stationary point of a multi-variable function, which of the following is true? |
| A. | Curl of the function becomes unity |
| B. | Gradient of the function vanishes |
| C. | Divergence of the function vanishes |
| D. | Gradient of the function is maximum |
| Answer» C. Divergence of the function vanishes | |
| 16. |
The on-board rocket motor of a satellite of initial mass 2000 kg provides a specific impulse of 280 seconds. If this motor is fired to give a speed increment of 500 m/s along the direction of motion, the mass of propellant consumed is: |
| A. | 685 kg |
| B. | 333 Kg |
| C. | 1666Kg |
| D. | 167Kg |
| Answer» C. 1666Kg | |
| 17. |
An athlete starts running with a speed V0. Subsequently, his speed decreases by an amount that is proportional to the distance that he has already covered. The distance covered will be |
| A. | Linear in time |
| B. | Quadratic in time |
| C. | Exponential in time |
| D. | Logarithmic in time |
| Answer» D. Logarithmic in time | |
| 18. |
Which one of the following statements is true? |
| A. | The isentropic efficiency of a compressor is constant throughout the compressor |
| B. | Flow separation problems are more critical for the axial compressors than for the centrifugal compressors |
| C. | The pressure ratio of a centrifugal compressor approaches zero as the compressor mass flow rate approaches zero |
| D. | Centrifugal compressors are always designed with multiple stages |
| Answer» B. Flow separation problems are more critical for the axial compressors than for the centrifugal compressors | |
| 19. |
Which one of the following materials should be selected to design an axial flow turbine operating at high temperatures? |
| A. | Steel alloy |
| B. | Titanium alloy |
| C. | Nickel alloy |
| D. | Aluminum alloy |
| Answer» D. Aluminum alloy | |
| 20. |
For an impulse turbine with identical stages, the hot gas exits from the stator blades at the mean blade height at an absolute angle of 70 degrees with the axis of the turbine. If the absolute inlet blade angle with the axis of the turbine at the mean blade height for the rotor blades is 37 degrees, then the absolute exit blade angle with the axis of the turbine at the mean blade height of the rotor blades is |
| A. | 33 degrees |
| B. | 37 degrees |
| C. | 53 degrees |
| D. | 53.5 degrees |
| Answer» C. 53 degrees | |
| 21. |
Air enters through the eye of a centrifugal compressor with a stagnation temperature 300 K and exits the compressor with a stagnation temperature 424 K. If the isentropic efficiency of the compressor is 0.81 and the ratio of specific heats of the flowing gas (assumed as constant) is 1.4, then the pressure ratio across the compressor is |
| A. | 2.75 |
| B. | 5.60 |
| C. | 65.00 |
| D. | 228.00 |
| Answer» B. 5.60 | |
| 22. |
If horizontal tail area is increased while the elevator to horizontal tail area ratio is kept same, then |
| A. | both longitudinal static stability and elevator control power will increase |
| B. | only longitudinal static stability will increase |
| C. | only elevator control power will increase |
| D. | neither stability nor control power changes |
| Answer» B. only longitudinal static stability will increase | |
| 23. |
The laminar boundary layer over a large flat plate held parallel to the ffeestream is 5 mm thick at a point 0.2 m downstream of the leading edge. The thickness of the boundary layer at a point 0.8 m downstream of the leading edge will be |
| A. | 20 mm |
| B. | 10 mm |
| C. | 5 mm |
| D. | 2.5 mm |
| Answer» B. 10 mm | |
| 24. |
A turbulent boundary layer remains attached over a longer distance on the upper surface of an airfoil than does a laminar boundary layer, because |
| A. | the turbulent boundary layer is more energetic and hence can overcome the adverse pressure gradient better |
| B. | the laminar boundary layer develops more skin friction and hence slows down more rapidly |
| C. | turbulence causes the effective coefficient of viscosity to reduce, resulting in less loss of momentum in the boundary layer |
| D. | the turbulent boundary layer is thicker, hence the velocity gradients in it are smaller, therefore viscous losses are less |
| Answer» B. the laminar boundary layer develops more skin friction and hence slows down more rapidly | |
| 25. |
spring-mass-damper system is excited by a force F0sino)t. The amplitude at resonance is measured to be 1 cm. At half the resonant frequency, the amplitude is 0.5 cm. The damping ratio of the system is |
| A. | 0.1026 |
| B. | 0.3242 |
| C. | 0.7211 |
| D. | 0.1936 |
| Answer» E. | |
| 26. |
Wing A has a constant chord c and span b. Wing B is identical but has a span 4b. When both wings are operating at the same geometric angle of attack at subsonic speed, then: |
| A. | wings A and B produce the same lift coefficient |
| B. | wing A produces a smaller lift coefficient than wing B |
| C. | wing A produces a greater lift coefficient than wing B |
| D. | the freestream Mach number decides which wing produces the greater lift coefficient |
| Answer» B. wing A produces a smaller lift coefficient than wing B | |
| 27. |
Two airfoils of the same family are operating at the same angle of attack. The dimensions of one airfoil are twice as large as the other one. The ratio of the minimum pressure coefficient of the larger airfoil to the minimum pressure coefficient of the smaller airfoil is |
| A. | 4.0 |
| B. | 2.0 |
| C. | 1.0 |
| D. | 0.5 |
| Answer» D. 0.5 | |
| 28. |
Two pipes of constant sections but different diameters carry water at the same volume flow rate. The Reynolds number, based on the pipe diameter, is |
| A. | the same in both pipes |
| B. | is larger in the narrower pipe |
| C. | is smaller in the narrower pipe |
| D. | depends on the material of the pipes |
| Answer» C. is smaller in the narrower pipe | |
| 29. |
One of the criteria for high-speed airplanes is that the critical Mach number should be as high as possible. Therefore, high-speed subsonic airplanes are usually designed with |
| A. | thick airfoils |
| B. | thin airfoils |
| C. | laminar flow airfoils |
| D. | diamond airfoils |
| Answer» C. laminar flow airfoils | |
| 30. |
The Joukowskii airfoil is studied in aerodynamics because |
| A. | it is used in many aircraft |
| B. | it is easily transformed into a circle, mathematically |
| C. | it has a simple geometry |
| D. | it has the highest lift curve slope among all airfoils |
| Answer» C. it has a simple geometry | |
| 31. |
Across a normal shock |
| A. | both total temperature and total pressure decrease |
| B. | both total temperature and total pressure remain constant |
| C. | total pressure remains constant but total temperature decreases |
| D. | total temperature remains constant but total pressure decreases |
| Answer» E. | |
| 32. |
On which one of the following thermodynamic cycles does an ideal ramjet operate? |
| A. | The Rankine cycle |
| B. | The Brayton cycle |
| C. | The Carnot cycle |
| D. | The Otto cycle |
| Answer» C. The Carnot cycle | |
| 33. |
The drag divergence Mach number of an airfoil |
| A. | is a fixed number for a given airfoil |
| B. | is always higher than the critical Mach number |
| C. | is equal to the critical Mach number at zero angle of attack |
| D. | is the Mach number at which a shock wave first appears on the airfoil |
| Answer» C. is equal to the critical Mach number at zero angle of attack | |
| 34. |
Total pressure at a point is defined as the pressure when the flow is brought to rest |
| A. | adiabatically |
| B. | isentropically |
| C. | isothermally |
| D. | isobarically |
| Answer» C. isothermally | |
| 35. |
For an elastic anisotropic solid, the number of independent elastic constants in its constitutive equations is |
| A. | 2 |
| B. | 9 |
| C. | 21 |
| D. | 36 |
| Answer» B. 9 | |
| 36. |
Let an airplane in a steady level flight be trimmed at a certain speed. A level and steady flight at a higher speed could be achieved by changing |
| A. | engine throttle only |
| B. | elevator only |
| C. | throttle and elevator together |
| D. | rudder only |
| Answer» D. rudder only | |
| 37. |
For a fixed center of gravity location of an airplane, when the propeller is mounted on the nose of the fuselage |
| A. | longitudinal static stability increases |
| B. | longitudinal static stability decreases |
| C. | longitudinal static stability remains same |
| D. | longitudinal static stability is maximum |
| Answer» C. longitudinal static stability remains same | |
| 38. |
Two airplanes are identical except for the location of the wing. The longitudinal static stability of the airplane with low wing configuration will be |
| A. | more than the airplane with high wing configuration |
| B. | less than the airplane with high wing configuration |
| C. | same as the airplane with high wing configuration |
| D. | more if elevator is deflected |
| Answer» D. more if elevator is deflected | |
| 39. |
An airplane with a larger wing as compared to a smaller wing will necessarily have |
| A. | more longitudinal static stability |
| B. | less longitudinal static stability |
| C. | same longitudinal static stability |
| D. | more longitudinal static stability for an aft tail airplane if aerodynamic center of the larger wing is behind the center of gravity of the airplane |
| Answer» E. | |
| 40. |
For maximum range of a glider, which of the following conditions is true? |
| A. | lift to drag ratio is maximum |
| B. | rate of descent is minimum |
| C. | descent angle is maximum |
| D. | lift to weight ratio is maximum |
| Answer» B. rate of descent is minimum | |
| 41. |
The number of natural frequencies of an elastic beam with cantilever boundary conditions is |
| A. | 1 |
| B. | 3 |
| C. | 1000 |
| D. | Infinite |
| Answer» E. | |
| 42. |
An artificial satellite remains in orbit and does not fall to the earth because |
| A. | the centrifugal force acting on it balances the gravitational attraction |
| B. | the on-board rocket motors provide continuous boost to keep it in orbit |
| C. | its transverse velocity keeps it from hitting the earth although it falls continuously |
| D. | due to its high speed it derives sufficient lift from the rarefied atmosphere |
| Answer» D. due to its high speed it derives sufficient lift from the rarefied atmosphere | |
| 43. |
A spring-mass-damper system with a mass of 1 kg is found to have a damping ratio of 0.2 and a natural frequency of 5 rad/s. The damping of the system is given by |
| A. | 2 Ns/m |
| B. | 2 N/s |
| C. | 0.2 kg/s |
| D. | 0.2 N/s |
| Answer» C. 0.2 kg/s | |
| 44. |
Consider the following system of linear equations: 2x – y + z = 1 3x – 3y + 4z = 6 x – 2y + 3z = 4 This system of linear equations has |
| A. | no solution. |
| B. | one solution. |
| C. | two solutions. |
| D. | three solutions |
| Answer» B. one solution. | |
| 45. |
The load factor of an aircraft turning at a constant altitude is 2. The coefficient of lift required for turning flight as compared to level flight at the same speed will be |
| A. | same |
| B. | half |
| C. | Double |
| D. | Four Times |
| Answer» D. Four Times | |
| 46. |
The pitch angle and the angle of attack for a fixed wing aircraft are equal during |
| A. | wings level constant altitude flight. |
| B. | unaccelerated climb. |
| C. | unaccelerated descent. |
| D. | landing. |
| Answer» B. unaccelerated climb. | |
| 47. |
Indicated airspeed is used by a pilot during |
| A. | take-off |
| B. | navigation |
| C. | setting the engine RPM. |
| D. | setting the elevator angle. |
| Answer» B. navigation | |
| 48. |
During an aircraft cruising flight, the altitude above the ground is usually measured using |
| A. | dynamic pressure |
| B. | static pressure. |
| C. | radar |
| D. | laser range finder. |
| Answer» C. radar | |
| 49. |
The damping ratio in phugoid motion for gliders is usually less compared to powered aircraft because |
| A. | gliders are unpowered. |
| B. | gliders are light |
| C. | lift to drag ratio is higher for gliders. |
| D. | gliders fly at low speed. |
| Answer» D. gliders fly at low speed. | |
| 50. |
For a given chamber pressure, the thrust of a rocket engine is highest when |
| A. | the rocket is operating at its design altitude. |
| B. | the rocket is operating in vacuum |
| C. | the rocket is operating at sea-level. |
| D. | there is a normal shock in the rocket nozzle. |
| Answer» C. the rocket is operating at sea-level. | |