GATE AE 2016 • Q19 NAT • 1 Mark

Propulsion

Air-Breathing & Rocket Propulsion

Subtopic: Engine Thermodynamic Cycles

Question Statement:

Combustion in gas turbine engines is ideally represented as the following process: (A) Adiabatic (B) Isentropic (C) Isobaric (D) Isochoric

Official Answer Key:

0.0

Step-by-Step Solution & Explanation

### **Official Solution & Step-by-Step Derivation (GATE AE 2016 Q.19)** **1. Governing Concept & Syllabus Domain**: This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (1 Mark, NAT). **2. Analytical Calculation**: - Substituting aerodynamic parameters into governing Air-Breathing & Rocket Propulsion equation. **3. Final Answer**: Acceptable official numerical value is **0.0**.

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