Desenvolvimento de uma metodologia para caracterização de perfil de asa para aeronave de baixa velocidade

Abstract

This work aims to develop and validate a methodology for aeroacoustic analysis and prediction of wing profiles using the ANSYS Fluent package. In addition, the study of the asymmetric profile GNEW5BP93B developed by NASA for electric aircraft. Currently, several studies have been carried out in order to provide the reduction of aircraft noise generated at the time of landing and take-off. The widely studied NACA 0012 wing profile was chosen for the validation of the methodology proposed in the present study. The aerodynamic simulation used the K-omega SST turbulent model for pressure, drag and lift coefficients. The results obtained were considered valid according to the results of experiments performed at NASA's Langley laboratory. After the aerodynamic validation, the transient condition URANS was used to obtain the acoustic results, until the condition close to the permanent condition RANS. Right after the numerical model reaches the quasi-permanent condition, it is validated through the acoustic theory of Ffowcs Williams and Hawkings; which is included in the ANSYS Fluent programa package. Having validated the methodology using the symmetrical profile NACA 0012, the asymmetrical profile GNEW5BP93B was used for the aerodynamic validation and acoustic prediction. The results showed that the NACA 0012 profile, which has lower drag coefficients, has lower sound pressure levels than the GNEW5BP93B profile for all simulated attack angles and frequency ranges. It was also found that the greater the angle of attack, the greater the drag and consequently the greater the noise generated in the symmetrical profile as well as in the asymmetrical profile.