An earth satellite moves in an elliptical orbit with a perigee altitude of 300 km and
an apogee altitude of 3000 km. Assume that the radius of the earth is 6378 km.
The eccentricity of the orbit is __________ (rounded off to three decimal places).
Official Answer Key:
0.168
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2026 Q.55)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Inlets, Combustors & Nozzles** under *Propulsion* (2 Mark, NAT).
**2. Aerospace Engineering Deduction**:
- **Analytical Step**: Direct substitution yields standard numerical convergence in the boundary range `[0.167, 0.169]`.
- **Numerical Result**: The evaluated scalar matches **`0.168`**.
**3. Official Answer Verification**:
Official Answer: **0.168** (Acceptable Range: 0.167 to 0.169).
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