Effect of an interface on transient temperature distribution in composite aircraft joints

Martin E. Barzelay, George F. Holloway
Apr 1957

Geometrically related structural joints representing typical skinstringer cross sections were tested under radiant heating to simulate the effects of aerodynamic heating. Temperature histories for 15 2024-T aluminum-alloy fabricated specimens and an equal number of integral control specimens were recorded for two different constant heat inputs, ranging from approximately 5 to 40 Btu/(sq ft) (sec).

An Adobe Acrobat (PDF) file of the entire report: