Ae GATE Scholarship Exam

  • GATE
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Quizzes Created: 9 | Total Attempts: 2,952
| Attempts: 182 | Questions: 65 | Updated: Mar 20, 2023
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About This Quiz
Ae GATE Scholarship Exam - Quiz

The AE GATE Scholarship Exam assesses advanced knowledge in aerospace engineering, focusing on dynamics of supersonic airplanes, structural mechanics, engine technology, and orbital mechanics. It prepares candidates for challenges in aerospace fields and higher studies.

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10. All professors are researchersSome scientists are professorsWhich of the given conclusions is logically valid and is inferred from the above arguments:(A) All scientists are researchers(B) All professors are scientists(C) Some researchers are scientists(D) No conclusion follows

Explanation

The given arguments state that all professors are researchers and that some scientists are professors. From these statements, it can be logically inferred that some researchers are scientists. This is because if all professors are researchers and some scientists are professors, then there must be a subset of professors who are also scientists, thus implying that some researchers are scientists. Therefore, the conclusion that some researchers are scientists is logically valid based on the given arguments.

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16. Following table gives data on tourists from different countries visiting India in the year 2011.Which two countries contributed to the one third of the total number of tourists who visited India in2011?(A) USA and Japan(B) USA and Australia(C) England and France(D) Japan and Australia

Explanation

England and France contributed to one third of the total number of tourists who visited India in 2011.

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17. Which one of the following shows the CORRECT variation of stagnation temperature along theaxis of an ideal ram jet engine?

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22. Consider the low earth orbit (LEO) and the geo synchronous orbit (GSO). Then(A) ∆V requirement for launch to LEO is greater than that for GSO, and altitude of LEO islower than that of GSO(B) ∆V requirement for launch to LEO is lower than that for GSO, and altitude of LEO islower than that of GSO(C) ∆V requirement for launch to LEO is greater than that for GSO, and altitude of LEO isgreater than that of GSO(D) ∆V requirement for launch to LEO is lower than that for GSO, and altitude of LEO isgreater than that of GSO 

Explanation

The correct answer is B. The explanation for this is that the ∆V requirement for launch to LEO is lower than that for GSO, and the altitude of LEO is lower than that of GSO. This means that it requires less energy (∆V) to launch a satellite into LEO compared to launching it into GSO. Additionally, LEO is at a lower altitude than GSO, which means that satellites in LEO are closer to the Earth's surface.

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28. A supersonic airplane is expected to fly at both subsonic and supersonic speeds during its wholeflight course. Which one of the following statements is TRUE?(A) Airplane will experience less stability in pitch at supersonic speeds than at subsonic speeds(B) Airplane will feel no change in pitch stability(C) Airplane will experience more stability in pitch at supersonic speeds than at subsonic speeds(D) Pitch stability cannot be inferred from the information given

Explanation

A supersonic airplane is expected to experience more stability in pitch at supersonic speeds than at subsonic speeds. This is because at supersonic speeds, the airflow over the wings becomes compressed and generates more lift, resulting in greater stability.

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30. Consider two engines P and Q. In P, the high pressure turbine blades are cooled with a bleed of 5% from the compressor after the compression process and in Q the turbine blades are not cooled. Comparing engine P with engine Q, which one of the following is NOT TRUE? (A) Turbine inlet temperature is higher for engine P(B) Specific thrust is higher for engine P(C) Compressor work is the same for both P and Q(D) Fuel flow rate is lower for engine P 

Explanation

The correct answer is D. Fuel flow rate is lower for engine P. This means that engine P consumes less fuel compared to engine Q. The statement is NOT TRUE because engine P actually requires a higher fuel flow rate due to the cooling of the high pressure turbine blades.

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32. For which one of the nozzle exit Mach numbers given below is the thrust highest? (A) 1(B) 1.5(C) 2(D) 2.5 

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The thrust of a nozzle is highest when the nozzle exit Mach number is equal to 2.5.

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37. The stiffened cross-section of a long slender uniform structural member is idealized as shown in the figure below. The lumped areas at A, B, C and D have equal cross-sectional area of 3 cm2.  The webs AB, BC, CD and DA are each 5 mm thick. The structural member is subjected to a twisting moment of 10 kNm. The magnitudes of the shear flow in the webs, qAB, qBC, qCD, and qDA in kN/m are, respectively(A) 20, 20, 20, 20(B) 0, 0, 50, 50(C) 40, 40, 0, 0(D) 50, 50, 50, 50 

Explanation

The correct answer is D because the shear flow in each web is directly proportional to the twisting moment and inversely proportional to the thickness of the web. Since the twisting moment is the same for all webs and the thickness of the webs is also the same, the shear flow in each web will be the same, which is 50 kN/m.

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40. The Headmaster ___________ to speak to you.Which of the following options is incorrect to complete the above sentence?(A) is wanting(B) wants(C) want(D) was wantingQ.58 Mahatama Gandhi was known

Explanation

The correct answer is (C) want. This option is incorrect because it does not match the subject-verb agreement. The subject "Headmaster" is singular, so the correct verb form should be singular as well. "Want" is the plural form of the verb, so it does not fit in this sentence. The correct verb form would be "wants," which is the singular form of the verb "want."

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43. A composite circular shaft is comprised of a steel core surrounded by an aluminum annulus,perfectly bonded to each other as shown in the figure. If it subjected to a pure torque, which one of the following statements is TRUE?(A) Only shear stress is continuous across the steel–aluminum interface(B) Only shear strain is continuous across the steel–aluminum interface(C) Both shear stress and shear strain are continuous across the steel–aluminum interface(D) Both shear stress and shear strain are discontinuous across the steel–aluminum interface

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46. For which one of the nozzle exit Mach numbers given below is the propulsive efficiency highest? (A) 1(B) 1.5(C) 2(D) 2.5  

Explanation

The propulsive efficiency of a nozzle is highest when the nozzle exit Mach number is equal to 1. At this Mach number, the flow velocity at the exit matches the speed of sound, resulting in the most efficient conversion of the high-pressure gas into kinetic energy. When the Mach number is less than 1, the flow is subsonic and the propulsive efficiency decreases. When the Mach number is greater than 1, the flow is supersonic and the propulsive efficiency also decreases. Therefore, option A with a nozzle exit Mach number of 1 has the highest propulsive efficiency.

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47. Minimum and maximum speeds of the airplane in level flight condition at sea-level in m/s arerespectively (A) 17.36 and 180(B) 17.36 and 34.22(C) 34.22 and 119.46(D) 17.36 and 119.46 

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The correct answer is C. The minimum and maximum speeds of the airplane in level flight condition at sea-level are 34.22 m/s and 119.46 m/s respectively.

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48. Mahatama Gandhi was known for his humility as(A) he played an important role in humiliating exit of British from India.(B) he worked for humanitarian causes.(C) he displayed modesty in his interactions.(D) he was a fine human being.

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Mahatma Gandhi was known for his humility because he displayed modesty in his interactions. This means that he did not boast about his achievements or put himself above others. Instead, he treated everyone with respect and kindness, regardless of their social status. Gandhi's humility was evident in his simple lifestyle, his willingness to listen to others, and his belief in the power of non-violence and peaceful resistance. Overall, his modesty and humility were key aspects of his character that endeared him to people and made him a respected leader.

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58. Distance of center of gravity of the aircraft ( XCG ) from the wing leading edge is(A) 0.447c (B) -0.547c (C) 0.547c (D) -0.25c 

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The correct answer is C. The distance of the center of gravity of the aircraft (XCG) from the wing leading edge is 0.547c.

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60. The airplane trim lift coefficient CL trim is (A) 0.502         (B) 0.402        (C) 0.302         (D) 0.202 

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All professors are researchersSome scientists are professorsWhich of...
Following table gives data on tourists from different countries...
Which one of the following shows the CORRECT variation of stagnation...
Consider the low earth orbit (LEO) and the geo synchronous orbit...
A supersonic airplane is expected to fly at both subsonic and...
Consider two engines P and Q. In P, the high pressure turbine blades...
For which one of the nozzle exit Mach numbers given below is the...
The stiffened cross-section of a long slender uniform structural...
The Headmaster ___________ to speak to you.Which of the following...
A composite circular shaft is comprised of a steel core surrounded by...
For which one of the nozzle exit Mach numbers given below is the...
Minimum and maximum speeds of the airplane in level flight condition...
Mahatama Gandhi was known for his humility as(A) he played an...
Distance of center of gravity of the aircraft ( XCG ) from the wing...
The airplane trim lift coefficient CL trim is (A)...
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