Aerodynamic Performance Optimization of a Single-Slotted Flap in Take-off using Artificial Neural Network (ANN)

This research aims to optimize the aerodynamic performance of the NACA-۲۳۰۱۲ airfoil equipped with a trailing edge high lift device. For this purpose, the flow simulation is done by solving the Navier-Stokes equations in a turbulent incompressible regime near the body. The chord-based Reynolds number is set to be Re=۳.۶×۱۰۶, therefore the k-ε turbulence model is employed for closure of the RANS equations. The simulations were performed for different values of gap and overlap with free stream velocity of ۳۱.۲ m/s, angles of attack and flap angle of ۱۰ and ۲۵ degrees, respectively. In this way, a primary database was generated, so, during a machine learning process using an artificial neural network on an initial database, a continuous response surface was produced in the design space. After generating the response surface, the optimal configuration was extracted.

کلیدواژه ها:

High-lift device ، Single Slotted Flap ، Aerodynamic Optimization ، Machine learning