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А.Ф. Киселев, В.В. Коваленко, Т.М. Притуло
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Инженерный журнал: наука и инновации
# 8·2017
Sonic boom investigation: Computation and experiment
© A.F. Kiselev, V.V. Kovalenko, T.M. Pritulo
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky town,
Moscow Region, 140180, Russia
The article deals with the issues related to designing supersonic aircraft. The biggest
hurdle in creating second-generation supersonic civil aircraft is the requirement for the
sonic boom amplitude to remain acceptable. The article presents results of investigating
the sonic boom phenomenon using a combined computational and experimental tech-
nique. The technique is based on measuring perturbed pressure in the near field of a
model mounted in the working part of a wind tunnel and subsequently remapping the
measurement data over large distances using the quasilinear theory. We provide results
of investigating pressure distributions in the near field of aircraft models in the TsAGI
T-113 wind tunnel. We compare experimental and numerical data and outline sugges-
tions for improving the technique.
Keywords:
supersonic civil aircraft, sonic boom, numerical techniques, mathematical
modelling, Zhilin's theorem, experimental techniques, near and far field
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