Aerodynamics
Shock Wave
Definition
A thin region of extremely rapid pressure and temperature increase that forms when airflow transitions from supersonic to subsonic. Normal and oblique shock waves increase drag dramatically at transonic and supersonic speeds.
Related Terms
Transonic
The speed regime between Mach 0.8 and 1.2 where both subsonic and supersonic air...
Compressibility
Effects that occur when air can no longer be treated as incompressible, typicall...
Critical Mach Number(Mcrit)
The Mach number at which airflow over some part of the aircraft first reaches th...
Test your knowledge
Think you understand Shock Wave? Challenge yourself with practice questions covering aerodynamics and all other ATPL subjects.
Start a Practice QuizOr browse all questions by subject