Features of the flow around the high-lift midwing aircraft

Аuthors

Bragin N. N.^1*, Zavarzina E. A.¹, Volkov A. I.², Krutov A. A.², Kuzin S. A.², Pigusov E. A.²

1. National Research Center "Zhukovsky Institut", 1, Zhukovsky str, Zhukovsky, Moscow Region, 140180, Russia
2. Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), Zhukovsky, Moscow region, Russia

*e-mail: braginnn@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:

integrated layout, civil aircraft, lift capability, computational investigations, flowing

References

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