It is well known in literature that further stages of flow separation and vortex breakdown around wings can be able to cause stall of wings. These formations must be investigated carefully for new plane types. However, some limited studies are available, especially on lambda wing for high angles of attack. In this study, effect of angle of attack on flow characteristics and vortex breakdown around a lambda wing is investigated with a constant Reynolds number of 10000. Computational fluid dynamic analysis is used and results of high angles of attack of the wing are given up to 45 0 which are not available in literature. Open water channel simulation is used. Vortex breakdown initially begins at an angle of 17 0 and it almost reaches to tip of wing when angle of attack is equal to 25 0. Vortices get stronger at further increments of angle of attack and they become to nearly equal length of wing at 45 0. Rounding effect of leading edges is investigated for decreasing vortex magnitudes. Streamline, particle injection, iso-value of vortices and location of stagnation points are given, and they are discussed in detail.
In addition to the commonly encountered force-body interaction problems, deformable body problems are frequently encountered in engineering applications and examination conditions are more complex. The friction force and contact pressure formed between the surfaces have dominant effects and mostly studies are investigated considering static and quasi-static conditions. However, considering the elastic/elastoplastic deformation and dynamic conditions, the geometric surface shape is important. In this study, using the finite element analysis method, the pressure distribution of the surfaces containing square, trapezoidal and circular surface shapes on a flat surface and the dynamic deceleration condition during the surface interaction of an object with initial velocity are investigated. The material used is steel whose ground geometry does not show linear behaviour and nylon material is used for surface geometry. In order to ensure that the surface effect is dominant in the dynamic examination, a linear increasing pressure is applied on the examined part. In the results, it was determined that there was an irregularity in the stress and velocity deceleration curve. The effect of compression pressure and friction coefficient has been examined in detail and the results are discussed.
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