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Numerical investigations of the asymmetry of a fluid flow in the channel of an air intake which is due to the interaction of a compression shock, generated by the shell ring of the air-intake channel, with the boundary layer on the longitudinally ribbed lower surface of this channel have been performed on the basis of the Reynolds-averaged Navier–Stokes equations and the SST k–ω model of turbulence. Data on the structure of the fluid flow in such a channel with a narrowing inlet part and a next part of constant cross section, the limiting flow lines on the longitudinally ribbed lower surface of the channel, and the profiles of the velocity of the flow and the total pressure in the boundary layer in the channel have been obtained for the case where the Mach number of the fluid flow incoming to the channel is M = 4. [ABSTRACT FROM AUTHOR]

Results of calculations of the sonic boom produced by a supersonic passenger aircraft in a cruising regime of flight at the Mach number M = 2.03 are presented. Consideration is given to the influence of the lateral dihedral of the wings and the angle of their setting, and also of different locations of the aircraft engine nacelles on the wing. An analysis of parametric calculations has shown that the intensities of sonic boom generated by a configuration with a dihedral rear wing and by a configuration with set wings remain constant, in practice, and correspond to the intensity level created by the optimum configuration. Comparative assessments of sonic boom for tandem configurations with different locations of the engine nacelles on the wing surface have shown that the intensity of sonic boom generated by the configuration with an engine nacelle on the windward side can be reduced by ~14% compared to the configuration without engine nacelles. In the case of the configuration with engine nacelles on the leeward size of the wing, the profile of the sonic-boom wave degenerates into an N-wave, in which the intensity of the bow shock is significantly reduced. [ABSTRACT FROM AUTHOR]