A solid propellant of density 1800 kg/m
3 has a burning rate law r = 6.65 x 10 -3p0.45 mm/s, where p
is pressure in Pascals. It is used in a rocket motor with a tubular grain with an initial burning area
of 0.314 m
2. The characteristic velocity is 1450 m/s. What should be the nozzle throat diameter to
achieve an equilibrium chamber pressure of 50 bar at the end of the ignition transient?
(A) 35 mm (B) 38 mm (C) 41 mm (D) 45 mm
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2012 Q.41)**
**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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