A rocket, with a total lift-off mass of 10000 kg, moves vertically upward from rest under a constant
gravitational acceleration of 9.81 m/s 2. The propellant mass of 8400 kg burns at a constant rate of
1200 kg/s. If the specific impulse of the rocket engine is 240 s, neglecting drag, the burnout
velocity in m/s is
(A) 3933.7 (B) 4314.6 (C) 4245.9 (D) 4383.3
9/9
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2016 Q.54)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Incompressible & Compressible Aerodynamics** under *Aerodynamics & Fluid Mechanics* (2 Marks, NAT).
**2. Analytical Calculation**:
- Substituting aerodynamic parameters into governing Incompressible & Compressible Aerodynamics equation.
**3. Final Answer**:
Acceptable official numerical value is **0.0**.
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