DESAIN PELURUS ALIRAN PADA SETTLING CHAMBER TEROWONGAN ANGIN SUPERSONIK

• Main Author: Wijaya, Marco
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/62014
• Institution: Institut Teknologi Bandung

Laboratory scale supersonic wind tunnel has been developed by Flight Physics Group, Faculty of Mechanical and Aerospace Engineering. This wind tunnel was designed to achieve Mach number equal to 2 in the test section, where the aerodynamics characteristics of an object to be tested. To obtain accurate measurement results, the uniform flow and low turbulence level are required. The previous numerical simulations showed that the flow quality is still below the standard. These are yielded because of the gas from the reservoir passes through the variable- diameter pipe and the turning pipes. Based on literature studies, the turbulence intensity should be approximately 1%. Therefore, the flow straightener devices/screens are needed in the settling chamber. Settling chamber and screen design are conducted by direct design and numerical method using commercial Computational Fluid Dynamics (CFD) software, named ANSYS CFX solved by Reynolds Averaged Navier Stokes approach and k-epsilon turbulence model. Domain decompositions use the hybrid grids, mixed between structured and unstructured. Some screen’s parameters were analyzed, such as opening angle of settling chamber, hole geometry, porosity, number, dan position of the screens. The computational domain for the simulations are straight pipe, settling chamber, and full configuration of supersonic wind tunnel. This research concludes that a screen with hexagonal hole geometry, 59% porosity, and applied at 2.5D is the best, by effectively reduces the turbulence intensity in the test section from 5.22% to 1.64%.