An aircraft is flying at Mach 3.0 at an altitude where the ambient pressure and temperature are 50
kPa and 200 K respectively. If the converging-diverging diffuser of the engine (considered
isentropic with ratio of specific heats, γ = 1.4 and specific gas constant R = 287 J/kgK) has a throat
area of 0.05 m2, the mass flow rate through the engine in kg/s is
(A) 197 (B) 232 (C) 790 (D) 157
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2014 Q.49)**
**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**.
Practice This in Real CBT Exam Interface
Test yourself with the official TCS-iON palette, virtual calculator, and immediate performance analytics.