Slow-crack-growth and indentation damage in calcium magnesium aluminosilicate (CMAS) glass from desert sand
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Free flight drag measurements on delta wing with wing-fuselage-store
The low-velocity impact response of graphite/epoxy laminates was investigated theoretically and experimentally. A nine-node isoparametric plate finite element in conjunction with an empirical contact law was used for the theoretical investigation. Theoretical results are in good agreement with strain-gage experimental data. The results of the investigation indicate that the present theoretical procedure describes the impact response of laminate for low-impact velocities.
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