Calculation of compressible turbulent boundary layers on bodies of revolution at supersonic speed = 초음속 유동에서 축대칭 물체 표면의 압축성 난류 경계층 계산

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Two dimensional and axisymmetric supersonic turbulent boundary layer with pressure gradient are calculated by using implicit finite difference method. Fluctuating terms in the equations are removed by using eddy viscosity and eddy conductivity concepts. Prandtl mixing length formulas are modified to account for pressure gradient and compressibility effects. The computational scheme used in the study is Keller Box Scheme which is efficient and accurate for this type of numerical calculation. Comparisons with published experimantal data show good agreements for boundary layers with favorable or mild adverse pressure gradient. And it is also found that the models of eddy viscosity and turbulent Prandtl number used in the study should be modified to account for the non-equiliblium flow effect of boundary layer developing rapidly with strong adverse pressure gradient.
Advisors
Lee, Dong-Ho이동호
Description
한국과학기술원 : 항공공학과,
Publisher
한국과학기술원
Issue Date
1983
Identifier
63627/325007 / 000811160
Language
eng
Description

학위논문(석사) - 한국과학기술원 : 항공공학과, 1983.2, [ [iii], 19, [21] p. ]

URI
http://hdl.handle.net/10203/26571
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=63627&flag=dissertation
Appears in Collection
AE-Theses_Master(석사논문)
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