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Influence of lift redistribution along the length of a supersonic airplane on the acoustic-shock parameters

Fomin, V. ; Volkov, V. ; Chirkashenko, V.

Journal of Engineering Physics and Thermophysics, 2007, Vol.80(5), pp.874-884 [Periódico revisado por pares]

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  • Título:
    Influence of lift redistribution along the length of a supersonic airplane on the acoustic-shock parameters
  • Autor: Fomin, V. ; Volkov, V. ; Chirkashenko, V.
  • Assuntos: Airplanes
  • É parte de: Journal of Engineering Physics and Thermophysics, 2007, Vol.80(5), pp.874-884
  • Descrição: Results of numerical investigations of the influence of lift redistribution along the length of the airframe of an airplane arrangement on the parameters of the acoustic shock produced by this arrangement and its aerodynamic characteristics are presented. The airplane arrangements investigated were constructed by disposition of wings in tandem at definite values of the aerodynamic lift and the lifting-surface area. The gasdynamic parameters of the flow near an arrangement were calculated by the numerical scheme based on the integral Euler equations, and the disturbed-pressure distribution at a large distance from the arrangement was determined using the quasi-linear theory. It is shown that the acoustic-shock level is substantially decreased in the case where there arises a middle-zone effect and an excess-pressure profile with an N-like shape. The arrangement of a supersonic airplane of weight 40 t making a cruise at a height H = 18 km and a Mach number M ∞ = 2.0, which makes it possible to decrease the acoustic shock produced by this airplane with no decrease in its lift-drag ratio, was determined.
  • Idioma: Inglês

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