Numerical and experimental investigation of the hypersonic flow structure in a complex flat duct

14 / 15

processes and gas dynamic effects. The resolution of the numerical results
is significantly higher, thus the flow can be investigated in more detail.
The research was conducted in the framework of the Russian Federation
President’s grant MK-5324.2014.1 in support of young Russian scientists.
REFERENCES
[1] Borovoy ., Egorov I.V., Noev . Two-dimensional interaction of falling
shock wave with turbulent boundary layer in presence of entropy layer. Mekhanika
zhidkosti i gaza [Fluid Dynamics], 2011, no. 6, pp. 88–109. (in Russ.).
[2] Gerasimov S.I., Faykov Yu.I., Kholik S.A. Kumulyativnye istochniki sveta
[Cumulative light sources]. Sarov, FGUP “RFYaTs-VNIIEF” Publ., 2011. 327 p.
[3] Gerasimov S.I., Faykov Yu.I. Tenevoe fotografirovanie v raskhodyashchemsya
puchke sveta [Shadow photography in divergent light beam]. Sarov, FGUP “RFYaTs-
VNIIEF”, 2010. 344 p. (in Russ.).
[4] Kovalev P.I., Mende N.P., eds. Al’bom sverkhzvukovykh techeniy [Catalogue of
supersonic flows]. SPb., Politekh. un-t Publ., 2011. 251 p.
[5] Krasnov I.F., Koshevoy V.N., Danilov A.N. Prikladnaya aerodinamika [Applied
aerodynamics]. Moscow, Vyssh. shk. Publ., 1974. 732 p.
[6] Zvegintsev V.I. Gazodinamicheskie ustanovki kratkovremennogo deystviya. Ch. 1.
Ustanovki dlya nauchnykh issledovaniy [Short-term gas-dynamic devices. Part 1].
Novosibirsk, Parallel’ Publ., 2014. 551 p.
[7] Kotov M.A., Ruleva L.B., Solodovnikov S.I., Surzhikov S.T. Experimental research
of the model flow-over in hypersonic aerodynamic shock tube. 5-ya Vseross.
shk.-seminar “Aerofizika i fizicheskaya mekhanika klassicheskikh i kvantovykh
sistem”. Sb. Nauch. Tr. [5th All-Russian School-Seminar “Aerophysics and Physical
Mechanics of Classical and Quantum Systems”: Proc. Sci. Int.]. Moscow, IPMekh
RAN, 2012, pp. 110–115 (in Russ.).
[8] Kotov M.A., Kuzenov V.V. Main trends in research of hypersonic flows in
aerodynamic shock tubes. Izobretatel’stvo , 2013, vol. XIII, no. 9, pp. 11–25 (in Russ.).
[9] Kotov M.A., Kryukov I.A., Ruleva L.B., Solodovnikov S.I., Surzhikov S.T.
Experimental Investigation of an Aerodynamic Flow of Geometrical Models in
Hypersonic Aerodynamic Shock Tube. AIAA 2013-2931. AIAA Wind Tunnel and
Flight Testing Aero II. 15 p.
[10] Kotov M.A., Kryukov I.A., Ruleva L.B., Solodovnikov S.I., Surzhikov S.T. Multiple
Flow Regimes in a Single Hypersonic Shock Tube Experiment. AIAA 2014-2657.
AIAA Aerodynamic Measurement Technology and Ground Testing Conference. 22 p.
[11] Gruber M.R., Baurle R.A., Mathur T., Hsu K.-Y. Fundamental Studies of Cavity-
Based Flame holder Concepts for Supersonic Combustors. J. of Propulsion and
Power, vol. 17, no. 1, 2001, pp. 146-153.
[12] Borovoy . Techenie gaza i teploobmen v zonakh vzaimodeystviya udarnykh voln
s pogranichnym sloem [Gas flow and heat exchange in interaction areas of shock
waves with boundary layer]. Moscow, Mashinostroenie Publ., 1983. 141 p.
[13] Barth T.J., Jespersen D.C. The design and application of upwind schemes on
unstructured meshes. AIAA Paper, No. 1989-0366, June 1989.
[14] Liou M.S., Steffen A New Flux Splitting Scheme. J. of Computational
Physics, 1993, vol. 107, pp. 23–39.
[15] Venkatakrishnan V. Convergence to Steady State Solutions of the Euler Equations
on Unstructured Grids with Limiters. J. of Computational Physics, 1995, vol. 118,
pp. 120–130.
ISSN 0236-3941. HERALD of the BMSTU. Series “Mechanical Engineering”. 2015. No. 1 17