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

Martin E. Barzelay, George F. Holloway
naca-tn-3824
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:
http://naca.central.cranfield.ac.uk/reports/1957/naca-tn-3824.pdf