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

巻 40, 発行 4, 2009, pp. 459-473
DOI: 10.1615/TsAGISciJ.v40.i4.50
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要約

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.

によって引用された
  1. Valiyev Kh. F., Kraiko A. N., Tillyayeva N. I., Simplification of Numerical and Analytical Tools for Sonic Boom Description, Computational Mathematics and Mathematical Physics, 62, 4, 2022. Crossref

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