A numerical study was undertaken to study the effect of the span wise injection on the performance of a 3D wing at a velocity of 15 m/s and angle of attack of 6°, 8°, and 10°. A baseline configuration along with injection at tip was studied. A study was conducted to understand the flow field and the winglet control techniques. Based on the study, a wing configuration was chosen as baseline configurations and different injection velocities were applied to this configuration. The chord wise pressure distribution is seen to change with the span wise location from the root and this distribution is affected by the wing tip vortex. The wingtip was observed to change the pressure distribution near the tip. The velocity field, stream lines and the vortices were seen to be affected by the presence of the injection. The lift and drag values were seen to decrease with the angle of attack but the l/d ratio remained nearly constant for all the injection configurations. Maximum reduction in drag of nearly 19% could be achieved with the injection. This study proved the possibility of using span wise injection as a control method to control the wing tip vortex.
Fibre-Wrapping using Fibre-Reinforced Plastic (FRP) shells is one of effective methods, significantly enhances the strength and ductility of concrete columns. The analysis is based on the behavior of the GFRP wrapped concrete columns under uniaxial compression. The compressive strength characteristics will consider for the study. The cross section of the concrete columns will be circular with diameter of 150mm and height 300mm. The strength determination is done experimentally and the results are verified by analytical method using ANSYS Civil FEM.
Tricycle arrangement landing gear is extensively used as it is simple; convenient both structurally as well as aerodynamically. Though it is advantageous over other configuration is has its own draw backs. Factors like its weight drag, sudden application of load, acoustics, fatigue etc tend to slow down its performance and life. Among main landing gear and nose landing gear; the former carries about 85% of total weight of aircraft and latter carries around 12-15% of weight. The nose landing gear is also a source of noise and its effect is prominent when compared to main landing gear. In this project the executive jet aircraft are studied thoroughly and a nose landing gear similar to those of executive jets is modeled using CATIA. The same geometry is imported to ANSYS ICEM and flow on the body is analyzed for different angle of attack. Pressure variation, temperature, density and velocity distribution around the body is noted and then Coefficient for Lift and Drag are plotted against angle of attack for obtained results. It is also important to check the strength and stiffness of designed landing gear. Hence using ANSYS APDL and Explicit; Static structural and Impact test has been carried out for designed geometry. Stress distribution and deformation was noted for two distinct materials such as steel and aluminum alloy and primary results of acoustics has been compared with the available data.
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