What is it about?
The static aeroelastic analysis of wind tunnel model has been carried out based on the one way fluid structure interaction methodology. For FSI analysis, loosely coupled approach is used to couple computational fluid dynamics (CFD) and computational structural dynamics (CSD) solvers. ANSYS Fluent and ANSYS Structural have been used to solve CFD and CSD problems respectively and ANSYS system coupling is used to couple CSD and CFD solvers. ANSYS Workbench platform has been used to do this analysis. The tests have been performed to investigate static aeroelastic responses by taking steady solution is an initial condition and at different Mach numbers for computational studies, the latest structural and CFD models of NASA are used. The designated output parameters such as steady aerodynamic lift, drag and moment coefficients are compared with the experimental data and obtained results from our study are matching well.
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Why is it important?
Fluid-structure interaction (FSI) is the phenomena, occurs when deformation caused by the fluid flow over a structure. Due to this deformation, there will be change in the boundary conditions of the fluid flow. This kind of interaction occurs in many natural phenomena and artificial engineering systems. One way FSI describes the pure mapping of physical properties obtained after the analysis using a fluid-model and a solid-model. Initially, solution for the fluid domain is calculated until the convergence criteria are reached. The option for reducing the computational time and cost of FSI simulations is the use of one-way coupled simulations. The calculated variables at the boundaries of the structure will be transferred to the structure side. Next, the solution on the structure side will be calculated until the convergence criterion is reached. No responses are feedback to the fluid model. Then, for the next time-step solution for the fluid domain is calculated till convergence.
Perspectives
The complete method has been developed to get solution for the static aeroelastic problem of the HIRENASD wing configuration and the obtained results are compared with the numerical results of NASA. The results of the present study appear to agree well with the results of NASA. Hence coupling procedure developed for Static aeroelastic analysis is in good agreement with the available results, same coupling procedure has been used to carry out dynamic aeroelastic analysis of HIRENASD configuration.
Mr. Dharmendra Ponnaswami
Dayananda Sagar Institutions
Read the Original
This page is a summary of: Static aero-elastic analysis of wind tunnel test model in transonic flow, January 2020, American Institute of Physics,
DOI: 10.1063/1.5141569.
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