A rocket operates at an absolute chamber pressure of 20 bar to produce thrust, Fଵ.
The hot exhaust is optimally expanded to 1 bar (absolute pressure) using a
convergent-divergent nozzle with exit to throat area ratio ቀ
ቁ of 3.5 and thrust
coefficient, Cி,ଵ =1.42.
The same rocket when operated at an absolute chamber pressure of 50 bar
produces thrust Fଶ and the thrust coefficient is Cி,ଶ.
Which of the following statement(s) is/are correct?
Options:
(A) Fଶ
Fଵ
= 2.5
(B) Fଶ
Fଵ
> 2.5
(C) Cி,ଶ
Cி,ଵ
= 1
(D) Cி,ଶ
Cி,ଵ
> 1
Official Answer Key:
A
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2022 Q.47)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (2 Marks, MSQ).
**2. Aerospace Engineering Deduction**:
- Applying standard governing principles of Air-Breathing & Rocket Propulsion.
- Option **(A)** matches the analytical derivation and official criteria.
**3. Final Answer**:
Correct Option is **(A)**.
Practice This in Real CBT Exam Interface
Test yourself with the official TCS-iON palette, virtual calculator, and immediate performance analytics.