Effect of SPA-model suspension assembly on the excess-pressure profile measured at a fixed distance from the source
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DOI: 10.1134/S0869864320020067
Effect of SPA-model suspension assembly on the excess-pressure profile measured at a fixed distance from the source* V.F. Volkov and T.A. Kiseleva Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia E-mail: [email protected]; [email protected] (Received July 1, 2019; revised July 1, 2019; accepted for publication November 6, 2019) Results of a physical experiment aimed at measuring the profile of relative excess pressure on a control surface in the near zone of the disturbed region of a schematized model of supersonic passenger aircraft (SPA) are reported. Tests in the test section of the T-313 wind tunnel, aimed at identification of the optimum mounting of SPA-model suspension and ensuring measurements of the full profile of the disturbed-pressure wave involving the leading, intermediate, and closing shock waves, were carried out. Comparisons of calculated data with experimental results are presented. Using the revealed optimum model suspension, measurement results in good agreement with the results of numerical calculations are obtained. The numerical solution to the problem about the flow around the geometric model was obtained and the necessary measurements in the experiment were carried out at freestream Mach number M∞ = 2.04 and angle of attack α = 4°. Keywords: supersonic flow, shock wave, rarefaction wave, sonic boom, tandem wing configuration, optimum suspension.
Introduction Developing supersonic passenger aircraft (SPA) with a reduced sonic boom (SB) level is accompanied by studies of the process of the formation and propagation of the SB wave. The main problem in simulating the SB is a very large extent of the region under study, in which the level of disturbed pressures varies by several orders of magnitude. There are various approaches to SB studies that include flight tests, experimental modeling of the phenomenon of interest in aeroballistic setups and wind tunnels, and numerical experiments. The main information obtained during the experimental SB studies is the disturbedpressure profiles generated by the model under testing. Since, in this case, it is the forced action of the disturbed flow on the environment that is of interest, it becomes necessary to determine the spatial distribution of the excessive (relatively undisturbed flow) static pressure behind the bow shock wave (BSW) at different distances from the model. This work was partially performed within the Program for Fundamental Scientific Research of the State Academies of Sciences for the years of 2013−2020 (Project No. АААА-А17-117030610137-0). *
V.F. Volkov and T.A. Kiseleva, 2020
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V.F. Volkov and T.A. Kiseleva
Given the large length of the flow under study, one can hardly simulate the entire process of formation of the SB wave under laboratory conditions. Flight experiment allows one to gain complete information about the parameters of the SB wave formed in the real atmosphere. However, at the stage of research concerning the development of aircraft conf
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