DEVELOPMENT, VERIFICATION, AND VALIDATION OF THE METHODOLOGY FOR SONIC BOOM OVERPRESSURE AND LOUDNESS CALCULATION USING MODERN COMPUTATIONAL FLUID DYNAMICS METHODS

摘要

Along with achievements in relation to the high aerodynamic characteristics during the supersonic cruising mode one of the main problems of creating new generation supersonic transport aircraft is providing acceptable sonic boom levels. This requires the development of reliable methods for obtaining the near field under the plane by taking into account the influence of the boundary layer in order to calculate the overpressure on the ground and evaluate the loudness of the sonic boom. In this work, a methodology used at TsAGI to calculate the sonic boom overpressure was adapted in the ANSYS CFX software package to solve the Reynolds-averaged Navier-Stokes equations. A macro to calculate the overpressure on the ground for the distribution of disturbances in the near field under the aircraft and a code to evaluate the sonic boom loudness in various metrics were developed. Computational mesh verification of the results was carried out and the methodology was validated using American Institute of Aeronautics and Astronautics Sonic Boom Prediction Workshop materials. Four variants of the equivalent body of revolution of the minimum sonic boom using nose part sharpening variations were investigated. The obtained overpressure curves were compared with the theoretical data and calculation results using Euler equations. The effect of sharpening the nose part on the aerodynamic drag and sound boom characteristics is shown.