For a given fuel flow rate and thermal efficiency, the take-off thrust for a gas turbine engine
burning aviation turbine fuel (considering fuel-air ratiof<<1) is
Options:
(A) Directly proportional to exhaust velocity
(B) Inversely proportional to exhaust velocity
(C) Independent of exhaust velocity
(D) Directly proportional to the square of the exhaust velocity
a
AE 3/11
AE (GATE 2014)
- AE
Official Answer Key:
A
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2014 Q.17)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (1 Mark, MCQ).
**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)**.
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