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LeadingEdge Flutter of Supercavitating Hydrofoils
https://resolver.caltech.edu/CaltechAUTHORS:BREjsr80
Authors: {'items': [{'id': 'BrennenCE', 'name': {'family': 'Brennen', 'given': 'C.'}}, {'id': 'OeyKT', 'name': {'family': 'Oey', 'given': 'K. T.'}}, {'id': 'BabcockCD', 'name': {'family': 'Babcock', 'given': 'C. D.'}}]}
Year: 1980
This paper presents the results of experiments and analysis of the phenomenon of leadingedge flutter which has been observed to occur for supercavitating hydrofoils. The experiments confirmed the existence of such a singledegreeoffreedom flutter involving chordwise bending and indicated that for long, natural (or vaporfilled) cavities the reduced flutter speed, [formula], was in the range 0.15 to 0.23. Secondary effects observed were the variation with the angle of attack (a minimum flutter speed occurred at 10 deg) and with foil mass ratio. Shorter cavities typically yielded lower flutter speeds due to a complex interaction between the bubble collapse process occurring in the cavity closure region and the unsteady hydrodynamic load on the foil. Finally, a relatively simple theoretical analysis for supercavitating hydrofoils with elastic axes aft of midchord is presented. This linear analysis yields reduced flutter velocities somewhat lower than those observed.
https://authors.library.caltech.edu/records/yya0gpt451

One dimensional modelling of failure in laminated plates by delamination buckling
https://resolver.caltech.edu/CaltechAUTHORS:CHAijss81
Authors: {'items': [{'id': 'ChaiH', 'name': {'family': 'Chai', 'given': 'Herzl'}}, {'id': 'BabcockCD', 'name': {'family': 'Babcock', 'given': 'Charles D.'}}, {'id': 'KnaussWG', 'name': {'family': 'Knauss', 'given': 'Wolfgang G.'}}]}
Year: 1981
DOI: 10.1016/00207683(81)900147
When low speed objects impact composite laminated plates delamination may result. Under inplane compression such delaminations may buckle and tend to enlarge the delaminated area which can lead to loss of global plate stability.
This process is modelled here in a first attempt by a delaminating beamcolumn wherein the local delamination growth, stability and arrest are governed by a fracture mechanicsbased energy release rate criterion.
https://authors.library.caltech.edu/records/rzp1g2dg89

Observation of Damage Growth in Compressively Loaded Laminates
https://resolver.caltech.edu/CaltechAUTHORS:CHAem83
Authors: {'items': [{'id': 'ChaiH', 'name': {'family': 'Chai', 'given': 'H.'}}, {'id': 'KnaussWG', 'name': {'family': 'Knauss', 'given': 'W. G.'}}, {'id': 'BabcockCD', 'name': {'family': 'Babcock', 'given': 'C. D.'}}]}
Year: 1983
An experimental program to determine tie phenomenological aspects of compositepanel failure under simultaneous compressive nplane loading and lowvelocity transverse impact [C75 m/s (0250 ft/s)] is described. Highspeed photography coupled with the shadowmoirĂ© technique is used to record the phenomenon of failure propagation. The information gained from these records, supplemented by plate sectioning and observation for interior damage, has provided information regarding the failurepropagation mechanism.
The results show that the failure process can be divided roughly into two phases. In the first phase the plane is impacted, and the resulting response causes interlaminar separation. In the second phase the local damage spreads to the undamaged portion of the plate through a combination of laminae buckling and further delamination.
https://authors.library.caltech.edu/records/tbbzht8v82

A Mechanical Model for Elastic Fiber Microbuckling
https://resolver.caltech.edu/CaltechAUTHORS:WAAjam90
Authors: {'items': [{'id': 'WaasAM', 'name': {'family': 'Waas', 'given': 'A. M.'}, 'orcid': '0000000252582749'}, {'id': 'BabcockCD', 'name': {'family': 'Babcock', 'given': 'C. D., Jr.'}}, {'id': 'KnaussWG', 'name': {'family': 'Knauss', 'given': 'W. G.'}}]}
Year: 1990
A twodimensional mechanical model is presented to predict the compressive strength of unidirectional fiber composites using technical beam theory and classical elasticity. First, a single fiber resting on a matrix halfplane is considered. Next, a more elaborate analysis of a uniformly laminated, unidirectional fiber composite halfplane is presented. The model configuration incorporates a free edge which introduces a buckling mode that originates at the free edge and decays into the interior of the halfplane. It is demonstrated that for composites of low volume fraction (<0.3), this decay mode furnishes values of buckling strain that are below the values predicted by the Rosen (1965) model. At a higher volume fraction the buckling mode corresponds to a half wavelength that is in violation of the usual assumptions of beam theory. Causes for deviations of the model prediction from existing experimental results are discussed.
https://authors.library.caltech.edu/records/xwagkgen29