A bipropellant liquid rocket motor operates at a ch amber pressure of 40 bar with a nozzle throat
diameter of 50 mm. The characteristic velocity is 1540 m/s. If the fuel-oxidizer ratio of the
propellant is 1.8, and the fuel density is 900 kg/m
3, what should be the minimum fuel tank volume
for a burn time of 8 minutes
(A) 1.65 m3 (B) 1.75 m 3 (C) 1.85 m 3 (D) 1.95 m 3
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2012 Q.42)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (2 Marks, 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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