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TsAGI Science Journal

ISSN Imprimir: 1948-2590
ISSN On-line: 1948-2604

TsAGI Science Journal

DOI: 10.1615/TsAGISciJ.v40.i4.50
pages 459-473

ANALYSIS OF THE SONIC BOOM INTENSITY USING NEAR-FIELD PERTURBATION UNDER THE AIRCRAFT, CALCULATED BY MEANS OF THE NONLINEAR THEORY

Kyuchul Cho
Institute of KDC

RESUMO

A procedure of sonic boom profile prediction is formed based on calculation of the disturbed flow fields in the aircraft near-field while numerically solving the complete Navier–Stokes equations. The sonic boom calculation technique, developed at TsAGI by Yu. L. Zhilin et al., is the basis for the algorithm. Application of nonlinear methods of disturbed flow-field calculation enables consideration, to one extent or another, such factors influencing the sonic boom intensity as the nose bluntness, viscosity, nozzle jets of propulsion system, etc. As an example, the influence of the nozzle jets of the Tu-144 aircraft on the sonic boom profile is shown, and the calculation results are compared with the experimental ones.


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