#TITLE_ALTERNATIVE#
<p align="justify"> Airfoil wings have different design goals for different flying missions. Inverse design method is presented for an efficient design method for wing section to obtain an airfoil geometry shape corresponding to a specific aerodynamic performance profile. A given pre...
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| Main Author: | |
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| Format: | Final Project |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/27387 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | <p align="justify"> Airfoil wings have different design goals for different flying missions. Inverse design method is presented for an efficient design method for wing section to obtain an airfoil geometry shape corresponding to a specific aerodynamic performance profile. A given pressure distribution as a certain objective of design was approached iteratively by adding the geometric correction obtained from the pressure distribution error to the initial airfoil. The numerical code for the inverse design will be developed using elastic membrane concept with the variation of the number of optimum coordinate points for the program. <br />
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Genetic algorithm has been applied to optimize the target pressure distribution for inverse design method. The optimized target pressure distribution around airfoil is obtain by parameterization and drag is minimized under several constraint on lift, pitching moment, airfoil thickness, etc. The airfoil geometries that corresponds with optimized target pressure distribution will be computed and evaluated by an inverse design code coupled with flow solver, XFOIL. <br />
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The final performance inverse design will be evaluated by FLUENT and the aerodynamic characteristics of designed airfoil were compared with the experiment result. <p align="justify"> <br />
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