Discussion
Match each term in List I with its definition in List II.
List I
A. Critical Mach number
B. Drag-divergence Mach number
C. Mach angle
D. Stagnation temperature
List II
1. Where drag begins to rise sharply in transonic flow
2. Where sonic flow first appears on the surface
3. The temperature after an adiabatic deceleration to rest
4. The half-angle of the cone bounding weak disturbances
Select the correct match.
Answer: B
The critical Mach number marks the first appearance of sonic flow anywhere on the body, and drag divergence follows a little later once the supersonic pocket ends in a strong enough shock. The Mach angle bounds the region weak disturbances can reach, and stagnation temperature measures the total energy of the stream.
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