Airplane A and Airplane B are cruising at altitudes of 2 km and 4 km,
respectively. The free stream density and static pressure at altitude 2 km are
1.01 kg/m3 and 79.50 kPa, respectively, and at altitude 4 km, they are 0.82 kg/m3
and 61.70 kPa, respectively. The differential pressure reading from the pitot-static
tubes is 3 kPa for both the airplanes. Assuming incompressible flow, the ratio of
cruise speeds of Airplane A to Airplane B is ______.
(round off to two decimal places)
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2023 Q.34)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Incompressible & Compressible Aerodynamics** under *Aerodynamics & Fluid Mechanics* (1 Mark, 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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