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TsAGI Science Journal

ISSN Imprimir: 1948-2590
ISSN En Línea: 1948-2604

TsAGI Science Journal

DOI: 10.1615/TsAGISciJ.2020034238
pages 15-28

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

Vladlen Sergeevich Gorbovskoy
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
Andrei Vyacheslavovich Kazhan
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
Vyacheslav Gennadievich Kazhan
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
Viktor Vasilievich Kovalenko
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
Leonid Leonidovich Teperin
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
Sergei Leonidovich Chernyshev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region, Russia

SINOPSIS

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.

REFERENCIAS

  1. NASA, Low Boom Flight Demonstration, http://www.nasa.gov/lowboom, 2020.

  2. Japan Aerospace Exploration Agency, D-Send Project, http://www.aero.jaxa.jp/eng/research/frontier/ sst/d-send.html, 2019.

  3. RUMBLE H2020 Collaborative Project, https://rumble-project.eu, 2020.

  4. NASA 3rd AIAA Sonic Boom Prediction Workshop, https://lbpw.larc.nasa.gov, 2020.

  5. Chernyshev, S.L., Sonic Boom, Moscow, Russia: Nauka, 2011. (in Russian).

  6. Park, M. and Nemec, M., Near Field Summary and Statistical Analysis of the Second AIAA Sonic Boom Prediction Workshop, in Proc. of 35th AIAA Applied Aerodynamics Conference, p. 3256,2017.

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