PHAK · Chapter 5: Aerodynamics of Flight
FAA · Retrieved 2026-09-05
Educational reference; original Owl summariesAERODYNAMICS
Shock waves & wave drag
FLIGHT SCIENCE / CONCEPT REFERENCE
SCIENCEConditions & principles
A shock is a thin region of abrupt pressure, temperature and density change in compressible flow.
REFERENCE COVERAGE3 / 3 editorial sections
PROVENANCE1 linked source
LAST RETRIEVED2026-09-05
Editorial section coverage describes the article structure, not scientific validation or completeness.
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Source editions
PHAK · Chapter 5: Aerodynamics of Flight ↗Edition / snapshot: FAA-H-8083-25C, 2023Retrieved: 2026-09-05
Retrieval dates record when Owl obtained the data; they are not publication dates or proof that a specification is current. Where the edition contains only a snapshot date, the original publication date is not recorded.
01
Mechanism
Supersonic flow can decelerate through a shock, increasing entropy. Interaction with the boundary layer can produce separation.
02
Aircraft response
Wave drag, buffet and changes in pitching moment can arise around transonic conditions. The effect depends on the wing and operating state.
03
Context & interpretation
A shock is not simply a visible condensation cloud. Wing sweep and section design influence the local flow field.
Sources & context
Educational explanation of physical mechanisms. Aircraft-specific procedures, limitations and current weather information are separate references.