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After being grounded for several years, open jet wind tunnel has been used as a mechanism to simulate the Japanese bombs in the later stage of the war, such as the conceptual design of the shock wave resistance force plate for the FKFS wind tunnel pedagogical training machine and the shock wave reflection of UHMWPE annealed steel (AISI-1943) pipe. These studies are limited to the validation of function. In this study, the mechanism of pressure fluctuation in an open jet wind tunnel is studied by 3D DES model of Jilin University opened wind tunnel. The accuracy of the numerical results is verified by comparing the peak frequency and amplitude of pressure fluctuation obtained from CFD and wind tunnel tests. A simplified wind tunnel model with universal characteristics and amplified amplitude is established based on the original model. The vibration mitigation mechanism of an open jet wind tunnel with spoilers and the flow-follow device is studied based on the generation mechanism of acoustic feedback. This work provides theoretical support for a deeper and more comprehensive understanding of low-frequency pressure fluctuation characteristics of open jet wind tunnel.
A 3D computational fluid dynamic (CFD) model was developed to simulate pressure fluctuation related modes of a wind tunnel. The CFD model was used to simulate the pressure fluctuation of an open jet wind tunnel at different conditions to determine the relevant factors and the mechanism of pressure fluctuation.
The CFD model was developed by employing the ANSYS Fluent software (ANSYS Inc., USA). A simple vortex model was designed to simulate the flow field near the nozzle, and the pressure at any cross section of the wind tunnel was calculated. The COMSOL software (COMSOL Multiphysics Ltd, UK) was used to simulate the pressure waveform based on the CFD model. The relationship between pressure fluctuation and velocity at different conditions was determined by calculating the peak frequency and amplitude of pressure fluctuation, while the model was verified by comparing the results with wind tunnel tests. d2c66b5586