Question Statement:
Which of the following statements is/are TRUE regarding critical and drag
divergence Mach numbers of a wing?
Options:
-
(A) Critical Mach number is the minimum freestream Mach number for which sonic
condition is attained somewhere over the wing
-
(B) Drag divergence Mach number is always higher than the critical Mach number
-
(C) Drag divergence Mach number is the local Mach number over the wing at which
the drag increases drastically
-
(D) Critical Mach number is independent of the angle of attack
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2026 Q.29)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Linear Algebra & Differential Equations** under *Engineering Mathematics* (1 Mark, MCQ).
**2. Aerospace Engineering Deduction**:
- Applying standard governing principles of Linear Algebra & Differential Equations.
- Option **(A)** matches the analytical derivation and official criteria.
**3. Final Answer**:
Correct Option is **(A)**.
Practice This in Real CBT Exam Interface
Test yourself with the official TCS-iON palette, virtual calculator, and immediate performance analytics.
Launch CBT Mock Test