Abstract
The paper presents the calculation results of the flow features and longitudinal aerodynamic characteristics of the NASA X-59 QueSST low boom demonstrator. When developing a perspective supersonic civil aircraft, it is necessary to apply reliable methods for calculating aerodynamic characteristics. It is important to work out the methodological basis of calculation. The methodological basis of the research consisted in the use of modern computational gas dynamics methods and algorithms for calculating the sonic boom propagation to evaluate aircraft aerodynamic and environmental characteristics. Steady-state Reynolds-averaged Navier-Stokes equations closed by the SST turbulence model were solved. As a result, the flow patterns were obtained, the features of the flow around the aerodynamic configuration were revealed, and the aerodynamic characteristics were estimated.
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