GATE AE 2013 • Q13
MCQ • 1 Mark
Aerodynamics & Fluid Mechanics
Incompressible & Compressible Aerodynamics
Subtopic: Airfoil & Wing Theory
Question Statement:
Consider a thin flat plate airfoil at a small angle to an oncoming supersonic stream of air.
Assuming the flow to be inviscid, 2
d
l
C
C
is
Options:
-
(A) zero
-
(B) independent of
-
(C) proportional to
-
(D) proportional to 2
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2013 Q.13)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Incompressible & Compressible Aerodynamics** under *Aerodynamics & Fluid Mechanics* (1 Mark, MCQ).
**2. Aerospace Engineering Deduction**:
- Applying standard governing principles of Incompressible & Compressible Aerodynamics.
- Option **(A)** matches the analytical derivation and official criteria.
**3. Final Answer**:
Correct Option is **(A)**.
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