#TITLE_ALTERNATIVE#
In transonic flow condition, the shock wave boundary layer interaction(SWBLI) and flow separation on wing upper surface of a civil aircraft induce transonic drag divergence. The transonic flow in case of a large drag caused by wave drag. The cause of wave drag are the strong shocks developing on the...
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| Format: | Final Project |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/15955 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | In transonic flow condition, the shock wave boundary layer interaction(SWBLI) and flow separation on wing upper surface of a civil aircraft induce transonic drag divergence. The transonic flow in case of a large drag caused by wave drag. The cause of wave drag are the strong shocks developing on the upper side of the wing creating an increase in entropy as well as an increase in boundary layer thickness eventually leading to separation. Thus, the final task of this research is numerically using FLUENT Computational Fluid Dynamics (CFD) software to determine the potential for drag reduction by making modifications to add AGSC4 Airfoil Shock Control Bump (SCB) on the surface of the Airfoil. SCB is useful to reduce the shock strength (shock normal turn into λ-shock) and the adverse pressure gradient on the upper surface AGSC4 Airfoil, so that it can to reduce the flow separation caused by the interaction of strong shock with a boundary layer. Different positions and length and height bump were numerically investigated to optimize the results of drag reduction on AGSC4 airfoil. |
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