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Undergraduate honors paper--Mount Holyoke College, 2008. Dept of Biological Sciences. / Includes bibliographical references (leaves 112-118).

Thesis (Ph. D.)--Virginia Polytechnic Institute and State University, 1992. / Vita. Abstract. Includes bibliographical references (leaves 130-135). Also available via the Internet.

The flow at incidence to a slender delta wing with leading edge and secondary separation is considered. A potential flow model is constructed in which the spiral vortex sheets of the actual flow are replaced by concentrated vortices and flat vortex feeding sheets connecting them with the separation lines. The problem is then reduced to a two-dimensional one by the use of slender body theory and the assumptions of conical flow. The method of conformal mapping is employed to obtain the potential solution. The auxiliary boundary condition on each of the vortex systems is that it is force free. The resulting non-linear algebraic equations are solved numerically by means of an iterative method, and values for lift are obtained as a function of incidence. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate

Monitoring of structural integrity is critical in many fields today, and particularly so in the civil, mechanical and aerospace engineering industries. In the aerospace industry, appreciably sized and almost exclusively composite UAVs share the airspace with other aircraft. Such composite structures also pose numerous uncertainties to structural health monitoring and analysis techniques. This necessitates research into a methodology for practical and effective structural health monitoring techniques. This work presents a methodology for structural health monitoring and particularly delamination detection in composite wing structures. The approach uses experimental modal analysis with due consideration for the probabilistic effects of random variations in material and geometrical properties, for the purpose of a general and non wing-specific damage detection technique. A large number of composite material coupons were tested to determine statistical distributions of 2D orthotropic material properties, using an optical image correlation system to reduce the expense of testing. Uncertainties in the wing geometry arising from manufacturing variances were taken into consideration. The material properties of the foam spar and resin beadings were considered isotropic and deterministic. A finite element model of the wing was subsequently improved using a scanning laser vibrometer to conduct detailed experimental modal analyses of five wings, and a multi-model updating approach based on frequency and mode shape information was used to update selected sensitive material properties. Significant improvement was accomplished. Using the probabilistic material property database, a confidence region was established for wing mode shapes through a Monte Carlo procedure. It was shown that delamination effects are capable of perturbing the dynamic mode shapes beyond the confidence regions implied by the material uncertainties. This provides a basis for further development of a structural health monitoring methodology for composite structures, taking due account of the many uncertainties in the structure. / Dissertation (MEng)--University of Pretoria, 2011. / gm2013 / Mechanical and Aeronautical Engineering / unrestricted

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