TS PGECET 2026 Aerospace Engineering (AS) Question Paper: Download Answer Key with Solutions PDF

TS PGECET 2026 Aerospace Engineering (AS) Question Paper will be available for download here. JNTU Hyderabad on behalf of Telangana Council of Higher Education (TGCHE) is conducting TS PGECET 2026 AS exam on June 1 in Shift 2 from 2 PM to 4 PM. TS PGECET AS Question Paper consists of 120 questions for 120 marks to be attempted in 2 hours.

TS PGECET AS Question Paper 2026 is divided into 2 sections- Engineering Mathematics with 10 questions and Aerospace Engineering domain with 110 questions.
Each questions carries 1 mark each and there is no negative marking for incorrect answers.

Candidates can download TS PGECET 2026 AS Question Paper with Answer Key and Solution PDF from links provided below.

TS PGECET 2026 AS Question Paper with Solution PDF

TS PGECET AS Question Paper 2026	Download PDF	Check Solutions

TS PGECET 2026 Aerospace Engineering Question Paper

TS PGECET 2026 Exam Pattern

Particulars	Details
Exam Mode	Computer-Based Test(CBT)
Question Type	Multiple Choice Questions(MCQs)
Total Questions	120 Questions
Total Marks	120 Marks
Exam Duration	2 Hours
Marking Scheme	+1 mark for each correct answer
Negative Marking	No Negative Marking
Language of Paper	English

TS PGECET 2026 Preparation Strategy

TS PGECET Questions

1.
If a rocket engine produces 30 kN thrust operating at chamber pressure of 4 MPa with throat diameter of 100 mm, then the thrust coefficient of a rocket engine is:

0.96
0.85
0.92
0.94

View Solution

2.
The period from the instant the igniter receives its signal until a portion of the grain surface burns and produces hot gases is called as

flame-spreading interval
ignition time lag
chamber-filling interval
burning time

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3.
Which one of the following is not related to solid propellant rocket?

high density
control over oxidizer to fuel ratio (O/F) once ignited
simple in construction
specific impulse in the range of 210–290 s

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4.
Which one of the following blades is more suitable for better efficiency and stable for wider range of operation?

forward curved blades
radial blades
backward curved blades
straight blades

View Solution

5.
If \(\beta>90^\circ\), then the blade shapes are known as

forward curved blades
radial blades
backward curved blades
straight blades

View Solution

6.
The propellants, which exhibit negative values of burn rate over a certain range of pressure are known as

normal burning
plateau burning
mesa burning
quenching

View Solution

TS PGECET 2026 Aerospace Engineering (AS) Question Paper: Download Answer Key with Solutions PDF

TS PGECET 2026 AS Question Paper with Solution PDF

TS PGECET 2026 Exam Pattern

TS PGECET 2026 Preparation Strategy

TS PGECET Questions

1.
If a rocket engine produces 30 kN thrust operating at chamber pressure of 4 MPa with throat diameter of 100 mm, then the thrust coefficient of a rocket engine is:

2.
The period from the instant the igniter receives its signal until a portion of the grain surface burns and produces hot gases is called as

3.
Which one of the following is not related to solid propellant rocket?

4.
Which one of the following blades is more suitable for better efficiency and stable for wider range of operation?

5.
If \(\beta>90^\circ\), then the blade shapes are known as

6.
The propellants, which exhibit negative values of burn rate over a certain range of pressure are known as

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TS PGECET 2026 AS Question Paper with Solution PDF

TS PGECET 2026 Exam Pattern

TS PGECET 2026 Preparation Strategy

TS PGECET Questions

1.If a rocket engine produces 30 kN thrust operating at chamber pressure of 4 MPa with throat diameter of 100 mm, then the thrust coefficient of a rocket engine is:

2.The period from the instant the igniter receives its signal until a portion of the grain surface burns and produces hot gases is called as

3.Which one of the following is not related to solid propellant rocket?

4.Which one of the following blades is more suitable for better efficiency and stable for wider range of operation?

5.If \(\beta>90^\circ\), then the blade shapes are known as

6.The propellants, which exhibit negative values of burn rate over a certain range of pressure are known as

Comments

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1.
If a rocket engine produces 30 kN thrust operating at chamber pressure of 4 MPa with throat diameter of 100 mm, then the thrust coefficient of a rocket engine is:

2.
The period from the instant the igniter receives its signal until a portion of the grain surface burns and produces hot gases is called as

3.
Which one of the following is not related to solid propellant rocket?

4.
Which one of the following blades is more suitable for better efficiency and stable for wider range of operation?

5.
If \(\beta>90^\circ\), then the blade shapes are known as

6.
The propellants, which exhibit negative values of burn rate over a certain range of pressure are known as