Estimation of Surface Pressures over Wing using Surrogate Model

During the aircraft design process, a detailed aero data base is needed for aerodynamic analysis, structural analysis and development of flight control law. Present work aims to develop a process for generating the aero database by fusing data from different sources. Studies are carried out to develop surrogate pressure field over a wing from experiments, low fidelity and high-fidelity data. This surrogate pressure surface is helpful during preliminary design stage for aerodynamic, structural design and optimization studies. Experimental and computational data are used for generating the model. The well-known ONERA M6 wing is chosen in this research. The objectives were first to estimate the pressure in the unmeasured locations and extend the methodology with additional design variable of angle-of-attack. Response surface, Kriging and Co-Kriging methods are used in this research. The quadratic response surface method shows to have larger error. Kriging and Co-Kriging methods tries to minimize the error while predicting the values at sampled location. However, these methods need good initial guess for correlation function parameters to get close values at other locations.