Standard

Hypersonic flow of gas over a slender wing of variable shape. / Bogatko, V. I.; Grib, A. A.; Kolton, G. A.

In: Fluid Dynamics, Vol. 14, No. 4, 07.1979, p. 548-554.

Research output: Contribution to journal › Article › peer-review

Harvard

Bogatko, VI, Grib, AA & Kolton, GA 1979, 'Hypersonic flow of gas over a slender wing of variable shape', Fluid Dynamics, vol. 14, no. 4, pp. 548-554. https://doi.org/10.1007/BF01051255

APA

Bogatko, V. I., Grib, A. A., & Kolton, G. A. (1979). Hypersonic flow of gas over a slender wing of variable shape. Fluid Dynamics, 14(4), 548-554. https://doi.org/10.1007/BF01051255

Vancouver

Bogatko VI, Grib AA, Kolton GA. Hypersonic flow of gas over a slender wing of variable shape. Fluid Dynamics. 1979 Jul;14(4):548-554. https://doi.org/10.1007/BF01051255

Author

Bogatko, V. I. ; Grib, A. A. ; Kolton, G. A. / Hypersonic flow of gas over a slender wing of variable shape. In: Fluid Dynamics. 1979 ; Vol. 14, No. 4. pp. 548-554.

BibTeX

@article{c0c92d7ae22945faac6e7c372072c837,
title = "Hypersonic flow of gas over a slender wing of variable shape",
abstract = "In a formulation analogous to [1-3], a study is made of the flow of a uniform homogeneous hypersonic ideal gas over the windward side of a slender wing whose surface profile depends on the time. The problem is solved by the thin shock layer method [4]. The bow shock is assumed to be attached to the leading edge of the wing at at least one point. The corrections of the first approximation to the main {"}Newtonian{"} flow are found. For wings of finite aspect ratio, when the bow shock is attached along the whole of the leading edge of the wing, computational formulas are obtained for determining the parameters of the gas in the shock layer.",
author = "Bogatko, {V. I.} and Grib, {A. A.} and Kolton, {G. A.}",
year = "1979",
month = jul,
doi = "10.1007/BF01051255",
language = "English",
volume = "14",
pages = "548--554",
journal = "Fluid Dynamics",
issn = "0015-4628",
publisher = "Springer Nature",
number = "4",

}

RIS

TY - JOUR

T1 - Hypersonic flow of gas over a slender wing of variable shape

AU - Bogatko, V. I.

AU - Grib, A. A.

AU - Kolton, G. A.

PY - 1979/7

Y1 - 1979/7

N2 - In a formulation analogous to [1-3], a study is made of the flow of a uniform homogeneous hypersonic ideal gas over the windward side of a slender wing whose surface profile depends on the time. The problem is solved by the thin shock layer method [4]. The bow shock is assumed to be attached to the leading edge of the wing at at least one point. The corrections of the first approximation to the main "Newtonian" flow are found. For wings of finite aspect ratio, when the bow shock is attached along the whole of the leading edge of the wing, computational formulas are obtained for determining the parameters of the gas in the shock layer.

AB - In a formulation analogous to [1-3], a study is made of the flow of a uniform homogeneous hypersonic ideal gas over the windward side of a slender wing whose surface profile depends on the time. The problem is solved by the thin shock layer method [4]. The bow shock is assumed to be attached to the leading edge of the wing at at least one point. The corrections of the first approximation to the main "Newtonian" flow are found. For wings of finite aspect ratio, when the bow shock is attached along the whole of the leading edge of the wing, computational formulas are obtained for determining the parameters of the gas in the shock layer.

UR - http://www.scopus.com/inward/record.url?scp=0018492643&partnerID=8YFLogxK

U2 - 10.1007/BF01051255

DO - 10.1007/BF01051255

M3 - Article

AN - SCOPUS:0018492643

VL - 14

SP - 548

EP - 554

JO - Fluid Dynamics

JF - Fluid Dynamics

SN - 0015-4628

IS - 4

ER -

ID: 48961957