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On the supersonic flow over an axisymmetric step at an angle of attack. / Simonenko, M. M.; Guvernyuk, S. V.; Kuzmin, A. G.

In: AIP Conference Proceedings, Vol. 2027, 030023, 02.11.2018.

Research output: Contribution to journal › Conference article › peer-review

Harvard

Simonenko, MM, Guvernyuk, SV & Kuzmin, AG 2018, 'On the supersonic flow over an axisymmetric step at an angle of attack', AIP Conference Proceedings, vol. 2027, 030023. https://doi.org/10.1063/1.5065117

APA

Simonenko, M. M., Guvernyuk, S. V., & Kuzmin, A. G. (2018). On the supersonic flow over an axisymmetric step at an angle of attack. AIP Conference Proceedings, 2027, [ 030023]. https://doi.org/10.1063/1.5065117

Vancouver

Simonenko MM, Guvernyuk SV, Kuzmin AG. On the supersonic flow over an axisymmetric step at an angle of attack. AIP Conference Proceedings. 2018 Nov 2;2027. 030023. https://doi.org/10.1063/1.5065117

Author

Simonenko, M. M. ; Guvernyuk, S. V. ; Kuzmin, A. G. / On the supersonic flow over an axisymmetric step at an angle of attack. In: AIP Conference Proceedings. 2018 ; Vol. 2027.

BibTeX

@article{f9ca7d9381004f0296da4f3fb4c8d0fd,
title = "On the supersonic flow over an axisymmetric step at an angle of attack",
abstract = "The work addresses 3D supersonic flow over a stepped axisymmetric body with a nose cone. Dependencies of flow regimes on the angle of attack α and length L of the body part ahead of the step are studied. Experiments were conducted in the A-7 wind tunnel of the Research Institute of Mechanics, Moscow State University, at a free-stream Mach number of 3. The study reveals bands of the angle α and length L in which flow pressure on the leeward side of step increases with increasing α or L, and eventually it exceeds the pressure on the windward side. Numerical simulations are performed with a finite-volume solver on the basis of URANS equations. The supersonic flow structure at a given length L and angles of attack from 0 to 16°is scrutinized. The simulations unveil a supersonic jet propagating along the body leeward side. The jet is located between a pair of side vortices formed due to a development of the transversal flow separation. At α>5°and sufficiently large L, the supersonic jet impact creates a spot of anomalously high pressure on the leeward side of the step.",
author = "Simonenko, {M. M.} and Guvernyuk, {S. V.} and Kuzmin, {A. G.}",
year = "2018",
month = nov,
day = "2",
doi = "10.1063/1.5065117",
language = "English",
volume = "2027",
journal = "AIP Conference Proceedings",
issn = "0094-243X",
publisher = "American Institute of Physics",
note = "19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 ; Conference date: 13-08-2018 Through 19-08-2018",

}

RIS

TY - JOUR

T1 - On the supersonic flow over an axisymmetric step at an angle of attack

AU - Simonenko, M. M.

AU - Guvernyuk, S. V.

AU - Kuzmin, A. G.

PY - 2018/11/2

Y1 - 2018/11/2

N2 - The work addresses 3D supersonic flow over a stepped axisymmetric body with a nose cone. Dependencies of flow regimes on the angle of attack α and length L of the body part ahead of the step are studied. Experiments were conducted in the A-7 wind tunnel of the Research Institute of Mechanics, Moscow State University, at a free-stream Mach number of 3. The study reveals bands of the angle α and length L in which flow pressure on the leeward side of step increases with increasing α or L, and eventually it exceeds the pressure on the windward side. Numerical simulations are performed with a finite-volume solver on the basis of URANS equations. The supersonic flow structure at a given length L and angles of attack from 0 to 16°is scrutinized. The simulations unveil a supersonic jet propagating along the body leeward side. The jet is located between a pair of side vortices formed due to a development of the transversal flow separation. At α>5°and sufficiently large L, the supersonic jet impact creates a spot of anomalously high pressure on the leeward side of the step.

AB - The work addresses 3D supersonic flow over a stepped axisymmetric body with a nose cone. Dependencies of flow regimes on the angle of attack α and length L of the body part ahead of the step are studied. Experiments were conducted in the A-7 wind tunnel of the Research Institute of Mechanics, Moscow State University, at a free-stream Mach number of 3. The study reveals bands of the angle α and length L in which flow pressure on the leeward side of step increases with increasing α or L, and eventually it exceeds the pressure on the windward side. Numerical simulations are performed with a finite-volume solver on the basis of URANS equations. The supersonic flow structure at a given length L and angles of attack from 0 to 16°is scrutinized. The simulations unveil a supersonic jet propagating along the body leeward side. The jet is located between a pair of side vortices formed due to a development of the transversal flow separation. At α>5°and sufficiently large L, the supersonic jet impact creates a spot of anomalously high pressure on the leeward side of the step.

UR - http://www.scopus.com/inward/record.url?scp=85056342422&partnerID=8YFLogxK

U2 - 10.1063/1.5065117

DO - 10.1063/1.5065117

M3 - Conference article

AN - SCOPUS:85056342422

VL - 2027

JO - AIP Conference Proceedings

JF - AIP Conference Proceedings

SN - 0094-243X

M1 - 030023

T2 - 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018

Y2 - 13 August 2018 through 19 August 2018

ER -

ID: 36760026