The Computational Fluid Dynamics simulation and optimization of a 69-degree-deltawing model in a supersonic flow condition. The steady compressible Reynolds Averaged NavierStokes (RANS) equation using the inviscid Euler equations will be solved using the flow solver ANSYS Fluent. The CFD simulations will be compared to experimental and prior results before optimization begins. After simulation results compare well with AIAA sonic boom workshops provided data, a genetic algorithm will be created to optimize the deltawing to minimize the pressure disturbance . The study of temperature effects on the pressure disturbance will also be considered using the sBOOM code provided by NASA Langley Research Center
Mechanical Engineering and Material Sciences Independent Study
Date of Submission
Mitchell, James and Agarwal, Ramesh K., "Computational Fluid Dynamics Simulation and Optimization of 69-Degree-Delta Wing Model in Supersonic Flow" (2016). Mechanical Engineering and Materials Science Independent Study. 21.