Modern methodological approaches to calculation the sonic boom characteristics of supersonic civil aircrafts
Аuthors
1*, 2**1. Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia
2. National Research Center "Zhukovsky Institut", 1, Zhukovsky str, Zhukovsky, Moscow Region, 140180, Russia
*e-mail: vladlen.gorbovskoy@tsagi.ru
**e-mail: kazhanav@nrczh.ru
Abstract
The article presents mean methodological approaches to calculation pressure distribution near field for numerical investigation the sonic boom characteristics of supersonic civil aircrafts. Based on results of analysis investigation of effect of computational geometry field, type of boundary conditions and dimension of the computational grid to the sonic boom characteristics near field and the ground. Suggestions have been represented for statement of the problem computational simulation of flowing near field, computational grid generation and pressure distribution calculation near flight vehicle with methods computational flow dynamics, applying for ensuing calculation of extension sonic boom to the ground.
Keywords:
sonic boom, supersonic civil aircraft, numerical simulation, near field, soundReferences
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