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Influence of the Configuration Elements of a Model of a Supersonic Passenger Aircraft on the Parameters of Sonic Boom

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Journal of Engineering Physics and Thermophysics Aims and scope

The author gives results of parametric calculations of shock-boom levels in the case of flow with a free-stream Mach number of 2.03 past configurations of a supersonic aircraft. The calculations are aimed at investigating the influence of the relative position of basic elements and their geometric shape on the aerodynamic quality of the configuration and on the parameters of shock boom at great distances from the perturbation source. The geometric models of the configurations were formed by combining and joining component elements: the body, the front wing, and the rear tapered wing with root dogtooth extension. From an analysis of all the considered models of tandem configurations with account of the resolvability of shock waves in a perturbed profile compared to the monoplane configuration, the optimum configuration has been singled out that ensures a reduction of 24% in the intensity level of shock boom with an increase of 0.24% in its aerodynamic quality.

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Authors and Affiliations

  1. Federal State Budgetary Institution of Science “S. A. Khristianovich Institute of Theoretical and Applied Mechanics”, Siberian Branch of the Russian Academy of Sciences, 4/1 Institutskaya Str., Novosibirsk, 630090, Russia

    V. F. Volkov

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  1. V. F. Volkov
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Correspondence to V. F. Volkov.

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Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 90, No. 2, pp. 478–490, March–April, 2017.

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Volkov, V.F. Influence of the Configuration Elements of a Model of a Supersonic Passenger Aircraft on the Parameters of Sonic Boom. J Eng Phys Thermophy 90, 449–460 (2017). https://doi.org/10.1007/s10891-017-1585-y

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  • DOI: https://doi.org/10.1007/s10891-017-1585-y

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